Airworthiness Directive · Amendment 39-18799 · Air conditioning
BAE Systems (Operations) Limited
This AD applies to the airplanes identified in paragraphs (c)(1) and (c)(2) of this AD, certificated in any category, all serial numbers.
(1) BAE Systems (Operations) Limited Model BAe 146-100A, -200A, and -300A airplanes.
(2) BAE Systems (Operations) Limited Model Avro 146-RJ70A, 146-RJ85A, and 146-RJ100A airplanes.
We are superseding Airworthiness Directive (AD) 2012-16-08 for certain BAE Systems (Operations) Limited Model BAe 146 and Avro 146-RJ series airplanes. AD 2012-16-08 required repetitive inspections for bulging, surface anomalies, and cracking of the fuselage skin adjacent to the discharge valves, and repair and application of additional sealant in the affected area if necessary. This new AD retains the requirements of AD 2012-16-08, expands the applicability, and requires an additional one-time inspection for the presence of water traps/air driers to determine which airplanes must be inspected. This AD was prompted by reports of cracking and surface anomalies of the fuselage skin at the water trap/air drier unit of the forward discharge valve due to corrosion, and the determination that airplanes on which a certain auto-pressurization modification was incorporated during production were excluded from the applicability of AD 2012-16-08, but are also affected by this condition. We are issuing this AD to address the unsafe condition on these products.
This paragraph restates the requirements of paragraph (g) of AD 2012-16-08, with specific delegation approval language. For all airplanes except airplanes that have incorporated auto-pressurization modification HCM50259A during production: Within 12 months after September 18, 2012 (the effective date of AD 2012-16-08), do a detailed inspection to check for bulging, surface anomalies, and cracking of the fuselage skin adjacent to the discharge valve outlets (one frame fore and aft, one stringer above and below), in accordance with the Accomplishment Instructions of BAE Systems (Operations) Limited Inspection Service Bulletin ISB.21-162, Revision 1, dated September 16, 2010. Repeat the inspection thereafter at intervals not to exceed 24 months.
(1) If any bulging, surface anomalies, or cracking of the fuselage skin is found to be within the criteria defined in Subject 53-00-00, “Fuselage, General Description,” of Chapter 53, “Fuselage,” of the BAE SYSTEMS BAe 146 Series/AVRO 146-RJ Series Structural Repair Manual for Series 100-200, Revision 66, dated October 15, 2011 (for Model 146-100A and -200A, and Avro 146-RJ70A and 146-RJ85A airplanes); or Subject 53-00-00, “Fuselage, General Description,” of Chapter 53, “Fuselage,” of the BAE SYSTEMS BAe 146 Series/AVRO 146-RJ Series Structural Repair Manual for Series 300, Revision 44, dated October 15, 2011 (for Model 146-300A and Avro 146-RJ100A airplanes): Before further flight, repair the damage, in accordance with the Accomplishment Instructions specified in BAE Systems (Operations) Limited Inspection Service Bulletin ISB.21-162, Revision 1, dated September 16, 2010.
(2) If any bulging, surface anomalies, or cracking of the fuselage skin is found exceeding the criteria as specified by Subject 53-00-00, “Fuselage, General Description,” of Chapter 53, “Fuselage,” of the BAE SYSTEMS BAe 146 Series/AVRO 146-RJ Series Structural Repair Manual for Series 100-200, Revision 66, dated October 15, 2011 (for Model 146-100A and -200A, and Avro 146-RJ70A and 146-RJ85A airplanes); or Subject 53-00-00, “Fuselage, General Description,” of Chapter 53, “Fuselage,” of the BAE SYSTEMS BAe 146/AVRO 146-RJ Series Structural Repair Manual for Series 300, Revision 44, dated October 15, 2011 (for Model 146-300A and Avro 146-RJ100A airplanes): Before further flight, repair the condition according to a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or BAE Systems (Operations) Limited's EASA Design Organization Approval (DOA).
This paragraph restates the requirements of paragraph (h) of AD 2012-16-08, with no changes. For all airplanes except airplanes on which auto-pressurization modification HCM50259A was incorporated during production: Within 24 months after September 18, 2012 (the effective date of AD 2012-16-08), unless a repair has already been accomplished in accordance with paragraph (g) of this AD, apply additional PR1422A-2 or PR1764B-2 edge sealant between the water trap/air drier and the fuselage skin, in accordance with the Accomplishment Instructions of BAE Systems (Operations) Limited Inspection Service Bulletin ISB.21-162, Revision 1, dated September 16, 2010. Application of additional sealant does not constitute terminating action for the repetitive detailed inspections required by paragraph (g) of this AD. Accomplishment of a repair as required by paragraph (g) of this AD terminates the repetitive inspection requirements of paragraph (g) of this AD.
Within 12 months after the effective date of this AD, inspect the airplane to determine whether water traps/air driers are installed, in accordance with paragraph 2.C of BAE Systems (Operations) Limited Inspection Service Bulletin ISB.21-162, Revision 4, dated January 28, 2015 (“ISB.21-162 R4”). If there are no water traps/air driers installed on an airplane, then no further inspections are required by this AD, except as required by paragraph (n) of this AD.
For airplanes that have water traps/air driers installed, determined as required by paragraph (i) of this AD: Within 12 months after the effective date of this AD, accomplish a detailed visual inspection for bulging, surface anomalies, and cracking of the external fuselage skin adjacent to the discharge valve outlets (one frame bay fore and aft, one stringer above and below), in accordance with the Accomplishment Instructions of paragraph 2.C. of ISB.21-162 R4. Repeat the inspection of the external fuselage skin adjacent to the discharge valve outlets thereafter at intervals not to exceed 24 months. Accomplishing an inspection required by this paragraph terminates the inspections required by paragraph (g) of this AD.
If, during any detailed visual inspection required by paragraph (j) of this AD, any bulging, surface anomalies, or cracking is found, before further flight, accomplish the applicable corrective action as specified in paragraphs (k)(1) and (k)(2) this AD.
(1) If any bulging, surface anomalies, or cracking is found to be within the criteria as specified in the applicable service information specified in paragraph (k)(1)(i) or (k)(1)(ii) of this AD, before further flight, repair in accordance with the Accomplishment Instructions of paragraph 2.G. of ISB.21-162 R4.
(i) For Model BAe 146-100A and -200A airplanes, and Model Avro 146-RJ70A and 146-RJ85A airplanes: Subject 53-00-00, “Fuselage, General Description,” of Chapter 53, “Fuselage,” of the BAE SYSTEMS BAe 146 Series/AVRO 146-RJ Series Structural Repair Manual for Series 100-200, Revision 68, dated October 15, 2014.
(ii) For Model BAe 146-300A airplanes and Model Avro 146-RJ100A airplanes: Subject 53-00-00, “Fuselage, General Description,” of Chapter 53, “Fuselage,” of the BAE SYSTEMS BAe 146 Series/AVRO 146-RJ Series Structural Repair Manual for Series 300, Revision 46, dated October 15, 2014.
(2) If any bulging, surface anomalies, or cracking is found exceeding the criteria as specified in the applicable service information specified in paragraph (k)(1)(i) or (k)(1)(ii) of this AD, before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or BAE Systems (Operations) Limited's EASA DOA.
Within 24 months after the effective date of this AD, unless a repair has already been accomplished as required by paragraph (k) of this AD, apply additional sealant, in accordance with the Accomplishment Instructions of paragraph 2.C.(3) of ISB.21-162 R4. Application of additional sealant on an airplane does not constitute terminating action for the repetitive inspections required by paragraph (j) of this AD for that airplane.
Accomplishment of a repair on the forward (FWD) or aft (AFT) position as required by paragraph (k) of this AD constitutes terminating action for the repetitive inspections required by paragraph (j) of this AD for that FWD or AFT position.
For airplanes that do not have water traps/air driers installed, determined as required by paragraph (i) of this AD: If water traps/air driers are installed in service after the effective date of this AD, accomplish the actions required by paragraphs (j), (k), and (l) of this AD on that airplane within the applicable compliance times specified in paragraphs (j), (k), and (l) of this AD; except where paragraphs (j) and (l) of this AD refer to “the effective date of this AD,” this AD requires compliance within the specified compliance time after the installation of water traps/air driers.
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.
Appliances and equipment
