90-26-07 BRITISH AEROSPACE: Amendment 39-6834. Docket No. 90-NM-172-AD.
Applicability: All Model BAC 1-11 200 and 400 series airplanes, certificated in any category.
Compliance: Required as indicated, unless previously accomplished.
To prevent reduced structural capability of the glazing frame and possible rapid decompression of the airplane, accomplish the following:
A. For airplanes operating at a maximum cabin differential pressure of 7.5 pounds per square inch (psi): Prior to the accumulation of 20,000 landings on the glazing frame since new, or within 1,600 landings after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 1,600 landings, perform an internal and external visual inspection, or non-destructive testing (NDT) inspection, of the pilot's and co-pilot's direct view (DV) window aperture (flight deck side glazing frame at Pillars B and C), in accordance with the Accomplishment Instructions of BritishAerospace Alert Service Bulletin 53-A-PM5985, Issue 1, dated March 21, 1990.
B. For airplanes modified for operation above 7.5 psi to a maximum of 8.2 psi cabin differential pressure: Prior to the accumulation of 14,000 landings on the glazing frame since new, or within 1,100 landings after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 1,100 landings, perform an internal and external visual inspection, or non-destructive testing (NDT) inspection, of the pilot's and co-pilot's DV window aperture (flight deck side glazing frame at Pillars B and C), in accordance with the Accomplishment Instructions of British Aerospace Alert Service Bulletin 53-A-PM5985, Issue 1, dated March 21, 1990.
C. If cracks are found during the inspections required by paragraph A. and B. of this AD, prior to further flight, perform an eddy current inspection, in accordance with British Aerospace Alert Service Bulletin 53-A-PM5985, Issue 1, dated March21, 1990; and
1. For cracks equal to or less than 0.2 inch, damage may be blended out in accordance with Table 1 or Table 2 of the service bulletin, as appropriate.
2. All other cracks must be repaired in accordance with the Structural Repair Manual, as specified in Table 1 and Table 2 of the service bulletin, as appropriate; or repaired in a manner approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate; or the glazing frame must be replaced with a serviceable part.
3. If blending has been previously accomplished, all cracks must be repaired in accordance with the BAC 1-11 Structural Repair Manual, as specified in Table 1 or Table 2 of the service bulletin, as appropriate; or repaired in a manner approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate.
4. Following repair or replacement, the inspections specified in paragraphs A. and B. of this AD are still required.
D. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate.
NOTE: The request should be submitted directly to the Manager, Standardization Branch, ANM-113, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Manager, Standardization Branch, ANM-113.
E. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD.
All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to British Aerospace, PLC, Librarian for Service Bulletins, Dulles International Airport, P.O. Box 17414, Washington, D.C. 20041-0414. These documents may be examined at the FAA,Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington.
This amendment (39-6834, AD 90-26-07) becomes effective on January 16, 1991.