Airworthiness Directive · Amendment 39-16270 · Flight controls
The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER Series Airplanes
Superseded. A later AD replaced this one: AD 2010-17-19. Comply with the one in force.
This AD applies to all The Boeing Company Model 737-600, −700, −700C, −800, −900, and −900ER series airplanes; certificated in any category.
The FAA is superseding an existing airworthiness directive (AD) that applies to all The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes. The existing AD currently requires doing a detailed inspection of the inboard and outboard aft attach lugs of the left and right elevator control tab mechanisms for gaps between the swage ring and the aft attach lug, and between the spacer and the aft attach lug; trying to move or rotate the spacer using hand pressure; and replacing any discrepant elevator tab control mechanism, including performing the detailed inspection on the replacement part before and after installation. For certain airplanes, this new AD adds improved repetitive inspections for discrepancies of the inboard and outboard aft attach lugs of the left and right elevator control tab mechanisms, and replacement if necessary. For certain other airplanes, this new AD adds a one-time inspection for discrepancies of the inboard and outboard aft attach lugs of the left and right elevator control tab mechanisms, and replacement if necessary. For airplanes on which the elevator control tab mechanism is replaced with a certain mechanism, this AD requires repetitive inspections for discrepancies of the elevator control tab mechanism and replacement if necessary. Replacing the elevator control tab mechanism with a new, Boeing-built mechanism terminates the repetitive inspections. This AD results from a report of failure of the aft attach lugs on the left elevator tab control mechanism, which resulted in severe elevator vibration; this event occurred on an airplane on which the existing AD had been done. We are issuing this AD to detect and correct a loose bearing in the aft lug of the elevator tab control mechanism, which could result in unwanted elevator and tab vibration. Consequent structural failure of the elevator or horizontal stabilizer could result in loss of structural integrity and aircraft control.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
For Groups 1, 2, and 3; and Group 4, Configuration 2; as identified in Boeing Alert Service Bulletin 737-27A1296, dated March 12, 2010: At the applicable time specified in paragraph 1.E. Compliance of Boeing Alert Service Bulletin 737-27A1296, dated March 12, 2010, except as required by paragraph (i) of this AD, do a detailed inspection of the inboard and outboard aft attach lugs of the left and right elevator control tab mechanisms for gaps between the swage ring and the aft attach lug, and between the spacer and the aft attach lug; and try to move or rotate the spacer using hand pressure; in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737-27A1296, dated March 12, 2010. Doing the inspection required by paragraph (m) or (o) of this AD, as applicable, terminates the requirements of this paragraph.
(h) If, during accomplishment of the actions required by paragraph (g) of this AD, any gap is found between the swage ring and the aft attach lug, or between the spacer and the aft attach lug; or if the spacer moves or rotates: Before further flight, do the actions required by paragraphs (h)(1) and (h)(2) of this AD, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737-27A1296, dated March 12, 2010.
(1) Inspect the replacement elevator tab control mechanism for discrepancies, as specified in paragraph (g) of this AD; and, if no discrepancy is found, install the replacement elevator tab control mechanism.
(2) Re-inspect the installed elevator tab control mechanism, as required by paragraph (g) of this AD.
(i) Where Boeing Alert Service Bulletin 737-27A1296, dated March 12, 2010, specifies a compliance time after the date of the original issue of the service bulletin, this AD requires compliance within the specified compliance time after April 7, 2010 (the effective date of AD 2010-06-51).
An inspection done before April 7, 2010, according to Boeing Multi Operator Message Number MOM-MOM-10-0159-01B, dated March 10, 2010, is considered acceptable for compliance with the corresponding inspection specified in paragraph (g) of this AD.
At the applicable time specified in paragraph (k)(1) or (k)(2) of this AD: Submit a report of the findings (both positive and negative) of the inspections required by paragraph (g) of this AD to Boeing Commercial Airplanes Group, Attention: Manager, Airline Support, e-mail: rse.boecom@boeing.com. The report must include the inspection results including a description of any discrepancies found, the airplane line number, and the number of flight cycles and flight hours accumulated on the airplane. Under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements contained in this AD and has assigned OMB Control Number 2120-0056.
(1) If the inspection was done on or after April 7, 2010: Submit the report within 10 days after the inspection.
(2) If the inspection was done before April 7, 2010: Submit the report within 10 days after April 7, 2010.
For all airplanes: As of April 7, 2010, and until the effective date of this AD, no person may install an elevator tab control mechanism, part number 251A2430-(), on any airplane, unless the mechanism has been inspected before and after installation, in accordance with the requirements of paragraph (g) of this AD, and no discrepancies have been found. As of the effective date of this AD, comply with paragraph (u) of this AD.
For Group 1 airplanes, as identified in Boeing Alert Service Bulletin 737-27A1297, dated April 16, 2010: Except as required by paragraph (n) of this AD, within 12 days after the effective date of this AD, do a detailed inspection for discrepancies of the inboard and outboard aft attach lugs of the left and right elevator control tab mechanisms, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737-27A1297, dated April 16, 2010. Repeat the inspection thereafter at intervals not to exceed 300 flight hours until the replacement specified in paragraph (r) of this AD is done. Doing the initial inspection required by this paragraph terminates the requirements of paragraph (g) of this AD.
(n) For Group 1 airplanes as identified in Boeing Alert Service Bulletin 737-27A1297, dated April 16, 2010: Beginning 7 days after the effective date of this AD, no person may operate an airplane on an extended twin operations (ETOPS) flight unless the initial inspection required by paragraph (m) of this AD has been accomplished.
For Group 2, Configuration 1 airplanes as identified in Boeing Alert Service Bulletin 737-27A1297, dated April 16, 2010: Within 30 days after the effective date of this AD, do a one-time detailed inspection for discrepancies of the inboard and outboard aft attach lugs of the left and right elevator control tab mechanisms, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737-27A1297, dated April 16, 2010. Doing the inspection required by this paragraph terminates the requirements of paragraph (g) of this AD.
If, during any inspection required by paragraph (m), (o), or (q) of this AD, any discrepancy is found, before further flight, replace the elevator tab control mechanism by doing the actions specified in paragraphs (p)(1) and (p)(2) of this AD.
(1) Do a detailed inspection for discrepancies of the replacement elevator tab control mechanism; and, if no discrepancy is found, install the replacement elevator tab control mechanism; in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737-27A1297, dated April 16, 2010. If any discrepancy is found, then that elevator tab control mechanism cannot be installed and the actions specified in this paragraph must be done before further flight on another replacement elevator tab control mechanism.
(2) Re-inspect the installed elevator tab control mechanism using the inspection procedure specified in paragraph (o) of this AD.
For Group 2, Configuration 1 airplanes as identified in Boeing Alert Service Bulletin 737-27A1297, dated April 16, 2010, on which the elevator control tab mechanism is replaced with a mechanism other than a new, Boeing-built mechanism: Within 300 flight hours after doing the replacement, do a detailed inspection for discrepancies of the inboard and outboard aft attach lugs of the left and right elevator control tab mechanisms, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737-27A1297, dated April 16, 2010. Repeat the inspection thereafter at intervals not to exceed 300 flight hours until the replacement specified in paragraph (r) of this AD is done.
Replacing an elevator tab mechanism with a new, Boeing-built mechanism, as specified in paragraphs (r)(1) and (r)(2) of this AD, terminates the inspections required by paragraphs (m), (o), and (q) of this AD.
Note 1: Refer to paragraphs 3.B.7.b.(1)(a)1) and 3.B.7.b.(1)(a)2) of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-27A1297, dated April 16, 2010, to establish whether the mechanism is Boeing-built.
(1) Do a detailed inspection for discrepancies of the new, Boeing-built replacement elevator tab control mechanism; and, if no discrepancy is found, install the replacement elevator tab control mechanism; in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737-27A1297, dated April 16, 2010. If any discrepancy is found, then that elevator tab control mechanism cannot be installed and the actions specified in this paragraph must be done on another new, Boeing-built replacement elevator tab control mechanism.
(2) Re-inspect the installed elevator tab control mechanism using the inspection procedure specified in paragraph (o) of this AD.
At the applicable time specified in paragraph (s)(1) or (s)(2) of this AD: Submit a report of any findings (positive and negative) of the first inspection required by paragraphs (m), (o), and (q) of this AD, and any positive findings from the repetitive inspections required by this AD, to Boeing Commercial Airplanes Group, Attention: Manager, Airline Support, e-mail: rse.boecom@boeing.com. The report must include the inspection results including a description of any discrepancies found, the airplane line number, and the total number of flight cycles and flight hours accumulated on the airplane. Under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements contained in this AD and has assigned OMB Control Number 2120-0056.
(1) If the inspection was done on or after the effective date of this AD: Submit the report within 10 days after the inspection.
(2) If the inspection was done before the effective date of this AD: Submit the report within 10 days after the effective date of this AD.
If, during any inspection required by paragraph (m), (o), or (q) of this AD, any discrepancy is found, and if the inspection was done on or after the effective date of this AD: Within 30 days after the inspection, return the discrepant elevator tab control mechanism, and include a copy of the inspection report sent to Boeing, as specified in paragraph (s) of this AD, to: Spares Distribution Center, Attention: Manager, Airline Support, Repair Overhaul and Exchange Services, SSA 111, Boeing Commercial Airplane Group, 2201 South 142nd Street, Door W10, Seatac, Washington, USA, 98168.
For all airplanes identified in paragraph (c) of this AD: As of the effective date of this AD, comply with the conditions specified in paragraphs (u)(1) and (u)(2) of this AD.
(1) No person may install an elevator tab control mechanism, part number 251A2430-(), on any airplane, unless the mechanism has been inspected before and after installation using the inspection procedures specified in either paragraphs (p)(1) and (p)(2) of this AD, or in paragraphs (r)(1) and (r)(2) of this AD; and no discrepancies have been found.
(2) An elevator tab control mechanism, part number 251A2430-(), that is not a new, Boeing-built elevator tab control mechanism may be installed, provided that the mechanism is inspected using the inspection procedures specified in paragraph (m) of this AD within 300 flight hours after doing the installation, and that the inspection is repeated thereafter at the interval specified in paragraph (m) of this AD.
