Airworthiness Directive · Amendment 39-19069 · Fuselage
The Boeing Company Airplanes
This AD applies to all The Boeing Company Model 737-100, -200, and -200C series airplanes, certificated in any category.
We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-100, -200, and -200C series airplanes. This AD was prompted by a report of incidents involving fatigue cracking in transport category airplanes that are approaching or have exceeded their design service objective and a structural reevaluation that was conducted by the manufacturer. This AD requires revising the maintenance or inspection program, as applicable, to add supplemental inspections. This AD also requires inspections to detect cracks in each structural significant item (SSI), and repair of any cracked structure. We are issuing this AD to address the unsafe condition on these products.
Prior to reaching the compliance time specified in paragraph (h)(1), (h)(2), or (h)(3) of this AD, as applicable: Incorporate a revision into the maintenance or inspection program, as applicable, that provides no less than the required damage tolerance rating (DTR) for each SSI listed in Boeing Document D6-37089, “Supplemental Structural Inspection Document for Model 737-100/200/200C Airplanes,” Revision F, dated November 2015 (“Document D6-37089, Revision F”). The required DTR value for each SSI is listed in Document D6-37089, Revision F. The revision to the maintenance or inspection program must include, and must be implemented in accordance with, the procedures in Section 5.0, “Damage Tolerance Rating (DTR) System Application,” and Section 6.0, “SSI Discrepancy Reporting” of Document D6-37089, Revision F. Accomplishing the revision required by this paragraph terminates the actions required by paragraphs (a) and (b) of AD 98-11-04 R1, and paragraph (g) of AD 2008-08-23.
Perform an inspection in accordance with Document D6-37089, Revision F, to detect cracks of all structure identified in Document D6-37089, Revision F, at the time specified in paragraph (h)(1), (h)(2), or (h)(3) of this AD, as applicable. Repeat the inspection thereafter at the intervals specified in Document D6-37089, Revision F. Accomplishing an initial inspection required by this paragraph terminates the corresponding inspection required by paragraph (c) of AD 98-11-04 R1 and paragraph (h) of AD 2008-08-23.
(1) For SSIs on Model 737-100 and -200 series airplanes: Before the accumulation of 66,000 total flight cycles, at the next inspection required by Note 5 of AD 98-11-04 R1 (Note 5 of AD 98-11-04 R1 follows paragraph (c)(2) of AD 98-11-04 R1), or within 12 months after the effective date of this AD, whichever occurs later.
(2) For SSIs on Model 737-200C series airplanes not affected by cargo configuration: Before the accumulation of 66,000 total flight cycles, at the next inspection required by paragraph (h) of AD 2008-08-23, or within 12 months after the effective date of this AD, whichever occurs later.
(3) For SSIs on Model 737-200C series airplanes affected by cargo configuration: Before the accumulation of 46,000 total flight cycles, at the next inspection required by paragraph (h) of AD 2008-08-23, or within 12 months after the effective date of this AD, whichever occurs later.
(1) If any cracked SSI structure is found during any inspection required by paragraph (h) of this AD, repair before further flight using an FAA-approved method or using a method approved in accordance with the procedures specified in paragraph (l) of this AD. Within 18 months after repair, incorporate a revision into the maintenance or inspection program, as applicable, to include a damage-tolerance-based alternative inspection program for the repaired structure. Thereafter, inspect the affected structure in accordance with the alternative program. The inspection method and compliance times (i.e., threshold and repetitive intervals) of the alternative program must be approved in accordance with the procedures specified in paragraph (l) of this AD.
(2) If any repair or alteration to an SSI is found during any inspection required by paragraph (h) of this AD such that the repair or alteration affects your ability to accomplish the inspections required by paragraph (h) of this AD, within 18 months after the inspection compliance time, incorporate a revision into the maintenance or inspection program, as applicable, to include a damage tolerance based alternative inspection program for each affected SSI. Thereafter, inspect the affected structure in accordance with the alternative inspection program. The inspection method and compliance times (i.e., threshold and repetitive intervals) of the alternative inspection program must be approved in accordance with the procedures specified in paragraph (l) of this AD. Accomplishing an initial inspection required by this paragraph terminates the corresponding inspection required by paragraph (i) of AD 2008-08-23.
Accomplishing the revision required by paragraph (g) of this AD and all initial inspections required by paragraph (h) of this AD terminates all requirements of AD 98-11-04 R1 and AD 2008-08-23.
A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120-0056. Public reporting for this collection of information is estimated to be approximately 5 minutes per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: Information Collection Clearance Officer, AES-200.
