Airworthiness Directive · Amendment 39-14607 · Gulfstream Model GV and GV-SP Series Airplanes
Gulfstream Model GV and GV-SP Series Airplanes
This AD applies to all Gulfstream Model GV series airplanes, and Model GV-SP series airplanes having serial numbers (S/Ns) 5001 through 5052 inclusive; certificated in any category.
The FAA is adopting a new airworthiness directive (AD) for all Gulfstream Model GV and certain Model GV-SP series airplanes. This AD requires a one-time inspection of the left and right aileron and elevator actuators to determine the part and serial numbers of each actuator, repetitive inspections of suspect actuators to detect broken damper shafts, and replacement of any actuator having a broken damper shaft. This AD also requires that operators report any broken damper shaft they find to the FAA. This AD also requires a terminating action for the repetitive inspections. This AD results from reports of broken or cracked damper shafts within the aileron and elevator actuator assemblies. We are issuing this AD to prevent broken damper shafts, which could result in locking of an aileron or elevator actuator (hard- over condition), which would activate the hard-over protection system (HOPS), resulting in increased pilot workload and consequent reduced controllability of the airplane.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
The term “customer bulletin,” as used in this AD, means the Accomplishment Instructions of the applicable Gulfstream customer bulletins specified in Table 1 of this AD. Although the customer bulletins recommend completing and submitting the Service Reply Card or reporting compliance with the customer bulletin, those actions are not required by this AD.
| For— | For model— | Use— | Dated— |
|---|---|---|---|
| (1) Initial/repetitive inspections of and corrective actions for identified subject actuators | (i) GV-SP series airplanes (ii) GV-SP series airplanes (iii) GV series airplanes | Gulfstream G500 Customer Bulletin 4 Gulfstream G550 Customer Bulletin 4 Gulfstream GV Customer Bulletin 123 | August 23, 2004. August 23, 2004. August 23, 2004. |
| (2) Terminating replacement of subject actuators | (i) GV-SP series airplanes (ii) GV-SP series airplanes (iii) GV series airplanes | Gulfstream G500 Customer Bulletin 6 Gulfstream G550 Customer Bulletin 6 Gulfstream GV Customer Bulletin 124 | December 8, 2004. December 8, 2004. December 8, 2004. |
Within 500 flight hours after the effective date of this AD: Do a one-time inspection of the left and right aileron and elevator actuators to determine the part number (P/N) and S/N of each actuator, in accordance with the applicable customer bulletin.
If no actuator with a P/N and S/N listed in Table 1 “Serial Number Effectivity Table” of the applicable customer bulletin is identified during the inspection required by paragraph (g) of this AD, no further action is required by this AD, except as required by paragraph (l) of this AD.
(i) For any actuator identified during the inspection required by paragraph (g) of this AD with a P/N and S/N listed in Table 1 “Serial Number Effectivity Table” of the applicable customer bulletin, and for actuators for which the P/N or S/N is missing or unreadable: Before further flight, do a detailed inspection of the identified actuator to detect a broken damper shaft, in accordance with the applicable customer bulletin.
Note 1: For the purposes of this AD, a detailed inspection is: “An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required.”
(1) If no damper shaft is found broken: Repeat the inspection required by paragraph (i) of this AD thereafter at intervals not to exceed 500 flight hours, until the terminating replacement specified in paragraph (j) of this AD is accomplished.
(2) If any damper shaft is found broken: Before further flight, do the action specified in paragraph (i)(2)(i), (i)(2)(ii), or (j) of this AD, in accordance with the applicable customer bulletin.
(i) Replace the actuator with a new or serviceable actuator having a P/N and S/N listed in Table 1 “Serial Number Effectivity Table” of the applicable customer bulletin, provided the new or serviceable actuator has been inspected in accordance with the requirements of paragraph (i) of this AD. Thereafter, repeat the inspection required by paragraph (i) of this AD for that actuator at intervals not to exceed 500 flight hours, until the terminating replacement specified in paragraph (j) of this AD is accomplished.
(ii) Replace the actuator with a new or serviceable actuator having a new P/N listed in Table 2 “Retrofit Part Number Replacement Table” of the applicable customer bulletin. This replacement terminates the requirements of this paragraph for that actuator only.
Within 24 months after the effective date of this AD: Replace all identified suspect actuators with new or serviceable actuators having a new P/N listed in Table 2 “Retrofit Part Number Replacement Table” of the applicable customer bulletin. This replacement terminates the requirements of this AD, except as required by paragraph (l) of this AD.
Submit a report of any broken damper shafts to the Manager, Atlanta Aircraft Certification Office (ACO), FAA, One Crown Center, 1895 Phoenix Boulevard, suite 450, Atlanta, Georgia 30349; fax (770) 703-6097. The report must be done at the applicable time specified in paragraph (k)(1) or (k)(2) of this AD. The report must include the inspection date, the airplane model and S/N, the actuator position (left or right aileron or elevator), and the actuator P/N and S/N. Information collection requirements contained in this AD have been approved by the Office of Management and Budget (OMB) under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq.) and have been assigned OMB Control Number 2120-0056.
(1) If the inspection required by paragraph (i) of this AD is done after the effective date of this AD: Submit a report within 30 days after the inspection is done.
(2) If an inspection required by paragraph (i) of this AD was done before the effective date of this AD: Submit a report within 30 days after the effective date of this AD.
As of the effective date of this AD, no person may install an aileron or elevator actuator having a P/N and S/N specified in the applicable customer bulletin on any airplane, unless the actuator has been inspected according to paragraph (i) of this AD.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
Aircraft
