Airworthiness Directive · Amendment 39-18338 · Landing gear
Gulfstream Aerospace Corporation Airplanes
Superseded. A later AD replaced this one: AD 2018-12-07. Comply with the one in force.
This AD applies to Gulfstream Aerospace Corporation Model GVI airplanes, certificated in any category, serial numbers 6001 and 6003 through 6163 inclusive.
Note 1 to paragraph (c) of this AD: Model GVI airplanes are also referred to by marketing designations G650 and G650ER.
We are adopting a new airworthiness directive (AD) for certain Gulfstream Aerospace Corporation Model GVI airplanes. This AD requires repetitive breakaway torque checks and torqueing of the brake inlet self-sealing couplings. This AD also requires revising the airplane flight manual to include procedures to follow in the event of certain display indications. This AD was prompted by reports of the self- sealing couplings on the brake inlet fitting that have been found backed out of the fully seated position. We are issuing this AD to detect and correct inadequate torque on the self-sealing coupling. This condition could result in an unannounced total loss of braking capability on one or multiple brakes, which could result in a runway overrun or asymmetrical braking that can lead to a lateral runway excursion.
(1) Within 15 days after the effective date of this AD, perform a breakaway torque check and torque the brake inlet self-sealing couplings, in accordance with Part I of the Accomplishment Instructions of Gulfstream G650 Alert Customer Bulletin 4A, dated November 13, 2015; or Gulfstream G650ER Alert Customer Bulletin 4A, dated November 13, 2015; as applicable.
(2) Within 100 flight cycles after completing the actions required by paragraph (g)(1) of this AD, perform a breakaway torque check and torque the brake inlet self-sealing couplings, in accordance with Part II of the Accomplishment Instructions of Gulfstream G650 Alert Customer Bulletin 4A, dated November 13, 2015; or Gulfstream G650ER Alert Customer Bulletin 4A, dated November 13, 2015; as applicable. Repeat the actions thereafter at intervals not to exceed 100 flight cycles.
Within 15 days after the effective date of this AD, revise the Limitations section of the AFM to include the statement found in figure 1 to paragraph (h) of this AD. This may be done by inserting a copy of this AD into the AFM. When a statement identical to that in figure 1 to paragraph (h) of this AD has been included in the general revisions of the AFM, the general revisions may be inserted into the AFM, and the copy of this AD may be removed from the AFM.
Within 15 days after the effective date of this AD, revise the Limitations section of the AFM to include the statement found in figure 2 to paragraph (i) of this AD. This may be done by inserting a copy of this AD into the AFM. When a statement identical to that in figure 2 to paragraph (i) of this AD has been included in the general revisions of the AFM, the general revisions may be inserted into the AFM, and the copy of this AD may be removed from the AFM.
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
