AD 81-14-08
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Fokker Services | F27 Mark 050 | Airworthiness Directives; FOKKER B.V. Model F27 Airplanes |
| aircraft | Fokker Services | F27 Mark 100 | Airworthiness Directives; FOKKER B.V. Model F27 Airplanes |
| aircraft | Fokker Services | F27 Mark 200 | Airworthiness Directives; FOKKER B.V. Model F27 Airplanes |
| aircraft | Fokker Services | F27 Mark 300 | Airworthiness Directives; FOKKER B.V. Model F27 Airplanes |
| aircraft | Fokker Services | F27 Mark 400 | Airworthiness Directives; FOKKER B.V. Model F27 Airplanes |
| aircraft | Fokker Services | F27 Mark 500 | Airworthiness Directives; FOKKER B.V. Model F27 Airplanes |
| aircraft | Fokker Services | F27 Mark 600 | Airworthiness Directives; FOKKER B.V. Model F27 Airplanes |
| aircraft | Fokker Services | F27 Mark 700 | Airworthiness Directives; FOKKER B.V. Model F27 Airplanes |
Unsafe Condition
Inadvertent unlocking of Ipeco seats, failure of the right elevator center hinge fitting, structural integrity issues with cargo door latch mechanisms, improper operation of main passenger door emergency release mechanisms, main landing gear system operational issues, pitot static system malfunction, cable loom damage, and inadequate battery power to the main DC tie bus.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Inspect and modify bolt and tracklock stop block per Fokker Service Bulletin 25-47 within 100 hours time in service and every 50 hours thereafter until modified within 500 hours. Inspect and rework cargo door latch mechanism per SB 52-60 within 100 hours. Inspect for cracks and replace hinge fittings per SB 55-52 within 500 hours. Modify main passenger door emergency release per SB 52-61 within 100 hours. Replace main gear actuating ram retaining ring before 7,500 landings or within 500 landings after AD effective date. Modify pitot static system per SB 34-41 within 100 hours. Inspect and modify cable loom per SB 30-34 within 200 hours. Inspect and modify battery wiring per Special Instructions 76 within 100 hours.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within the next 100 hours time in service and every 50 hours thereafter until modified within 500 hours time in service (for seats). Within 100 hours time in service for cargo door, hinge fitting inspection, main passenger door, pitot static, and battery wiring. Within 200 hours for cable loom. Before 7,500 landings or within 500 landings after AD effective date for landing gear.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Fokker B.V. Model F27 airplanes, all series, with specific serial numbers as listed in each paragraph (A to H) of the AD.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Unlocking Of Ipeco Seats
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_81-14-08.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 81-14-08 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; FOKKER B.V. Model F27 Airplanes Subject: Unlocking Of Ipeco Seats Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 08/10/1981 Make: Fokker Services Model: F27 Mark 050 | F27 Mark 100 | F27 Mark 200 | F27 Mark 300 | F27 Mark 400 | F27 Mark 500 | F27 Mark 6...Show more Product Type: Aircraft Product Subtype: Large Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 81-14-08 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-4156 AD NUMBER: 81-14-08 SUBJECT HEADING: Airworthiness Directives; FOKKER B.V. Model F27 Airplanes ACTION: SUMMARY: DATES: Effective August 10, 1981. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 81-14-08 FOKKER B.V.: Amendment 39-4156. Applies to Model F27 airplanes, all series, certificated in all categories as indicated below. Unless already accomplished, accomplish the following within the time specified in each paragraph below after the effective date of this AD. A. Applies to airplanes S/N 10479, 10492, 10499, 10500, 10502, 10529, 10534, 10536 through 10557, 10559, 10561 through 10585. To prevent inadvertent unlocking of the Ipeco seats, inspect and modify the bolt and tracklock stop block in accordance with the Accomplishment Instructions of Fokker F27 Service Bulletin No. 25-47 dated January 1, 1979, or later FAA approved revisions. Perform this inspection within the next 100 hours time in service and every 50 hours thereafter until the bolt and tracklock stop block have been modified. The bolt and tracklock stop block are to be modified within the next 500 hours time in service. B. Applies to airplanes S/N 10572 and below equipped with a large cargo door identified by Fokker F27 Service Bulletin No. 52-60. To ensure the functional and structural integrity of the cargo door latch mechanism, within the next 100 hours time in service, inspect the latch mechanism and rework, as necessary, in accordance with the Accomplishment Instructions of Fokker F27 Service Bulletin No. 52-60 dated May 1, 1979, or later FAA approved revisions. C. Applies to airplanes S/N 10547 and below, 10558 and 10560. To prevent failure of the right elevator center hinge fitting, within 100 hours and every 100 hours thereafter until replaced, inspect for cracks in accordance with the F27 Structural Integrity Program, item 55-50- 01, Revision 1. Within the next 500 hours time in service, replace hinge fittings in accordance with the Accomplishment Instructions of Fokker F27 Service Bulletin No. 55-52, dated May 1, 1979, or later FAA approved revisions. D. Applies to airplane S/N 10102 through 10462 incorporating Fokker F27 Service Bulletin No. 52-47, 10464 through 10468, 10470 through 10477, 10484, 10486, 10498, 10501, 10503 through 10506, 10508, 10511 through 10515, 10519, 10521 through 10525, 10527, 10528, 10530 through 10535, 10539, 10545, 10550, 10551, 10552, 10554, 10557 through 10560, 10562, 10563, 10566, 10567, 10569, 10572, 10573, 10574, 10576, 10579, 10581, 10585 through 10589 and 10591. To ensure the operation of the main passenger door during an emergency evacuation, within the next 100 hours time in service after the effective date of this AD, modify the emergency release mechanism of the main passenger door in accordance with the Accomplishment Instructions of Fokker F27 Service Bulletin No. 52-61, dated January 2, 1980. E. Applies to all Fokker F27 airplanes having accumulated more than 7,000 landings. To ensure main landing gear system operation, prior to 7,500 landings or within 500 landings after the effective date of this AD, whichever comes later, replace main gear actuating ram retaining ring P/N ACM18254 with a serviceable retaining ring having less than 7,500 landings in accordance with the F27 Structural Integrity Program under item 32-30-01, Revision 1, subitem d or in accordance with the Accomplishment Instructions of Fokker F27 Service Bulletin No. 32-136, dated February 18, 1980, or later FAA approved revisions. (Note: Established life limits are not to be exceeded.) F. Applies to airplane S/N 10505 to 10547 inclusive and 10550. To ensure proper function of the pitot static system, within the next 100 hours time in service, modify the pitot static system in accordance with the Fokker F27 Service Bulletin No. 34-41, dated March 13, 1978, or later FAA approved revisions. G. Applies to airplane S/N 10299 to 10547 inclusive. To prevent damage to the cable loom, within the next 200 hours time in service, inspect and modify as necessary the cable loom in accordance with Fokker F27 Service Bulletin No. 30-34 dated April 17, 1978, or later FAA approved revisions. H. Applies to airplane S/N 10526, 10527, 10529, 10543, 10547, 10533, 10555, 10556, 10563, 10564, 10565, 10570, 10582 and 10583. To ensure airplane battery power to the main DC tie bus, within 100 hours time in service, inspect and modify as necessary the battery wiring to the battery reverse current circuit breakers in accordance with the Fokker F27 Special Instructions No. 76 dated November 20, 1978, or later FAA approved revisions. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. Alternate means of compliance or other actions which provide an equivalent level of safety may be used when approved by the Chief, Seattle Area Aircraft Certification Office, FAA Northwest Region. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). This amendment becomes effective August 10, 1981. FOOTER:
Document Text
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AD Final Rules - DRS_81-14-08.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 81-14-08 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; FOKKER B.V. Model F27 Airplanes Subject: Unlocking Of Ipeco Seats Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 08/10/1981 Make: Fokker Services Model: F27 Mark 050 | F27 Mark 100 | F27 Mark 200 | F27 Mark 300 | F27 Mark 400 | F27 Mark 500 | F27 Mark 6...Show more Product Type: Aircraft Product Subtype: Large Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 81-14-08 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-4156 AD NUMBER: 81-14-08 SUBJECT HEADING: Airworthiness Directives; FOKKER B.V. Model F27 Airplanes ACTION: SUMMARY: DATES: Effective August 10, 1981. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 81-14-08 FOKKER B.V.: Amendment 39-4156. Applies to Model F27 airplanes, all series, certificated in all categories as indicated below. Unless already accomplished, accomplish the following within the time specified in each paragraph below after the effective date of this AD. A. Applies to airplanes S/N 10479, 10492, 10499, 10500, 10502, 10529, 10534, 10536 through 10557, 10559, 10561 through 10585. To prevent inadvertent unlocking of the Ipeco seats, inspect and modify the bolt and tracklock stop block in accordance with the Accomplishment Instructions of Fokker F27 Service Bulletin No. 25-47 dated January 1, 1979, or later FAA approved revisions. Perform this inspection within the next 100 hours time in service and every 50 hours thereafter until the bolt and tracklock stop block have been modified. The bolt and tracklock stop block are to be modified within the next 500 hours time in service. B. Applies to airplanes S/N 10572 and below equipped with a large cargo door identified by Fokker F27 Service Bulletin No. 52-60. To ensure the functional and structural integrity of the cargo door latch mechanism, within the next 100 hours time in service, inspect the latch mechanism and rework, as necessary, in accordance with the Accomplishment Instructions of Fokker F27 Service Bulletin No. 52-60 dated May 1, 1979, or later FAA approved revisions. C. Applies to airplanes S/N 10547 and below, 10558 and 10560. To prevent failure of the right elevator center hinge fitting, within 100 hours and every 100 hours thereafter until replaced, inspect for cracks in accordance with the F27 Structural Integrity Program, item 55-50- 01, Revision 1. Within the next 500 hours time in service, replace hinge fittings in accordance with the Accomplishment Instructions of Fokker F27 Service Bulletin No. 55-52, dated May 1, 1979, or later FAA approved revisions. D. Applies to airplane S/N 10102 through 10462 incorporating Fokker F27 Service Bulletin No. 52-47, 10464 through 10468, 10470 through 10477, 10484, 10486, 10498, 10501, 10503 through 10506, 10508, 10511 through 10515, 10519, 10521 through 10525, 10527, 10528, 10530 through 10535, 10539, 10545, 10550, 10551, 10552, 10554, 10557 through 10560, 10562, 10563, 10566, 10567, 10569, 10572, 10573, 10574, 10576, 10579, 10581, 10585 through 10589 and 10591. To ensure the operation of the main passenger door during an emergency evacuation, within the next 100 hours time in service after the effective date of this AD, modify the emergency release mechanism of the main passenger door in accordance with the Accomplishment Instructions of Fokker F27 Service Bulletin No. 52-61, dated January 2, 1980. E. Applies to all Fokker F27 airplanes having accumulated more than 7,000 landings. To ensure main landing gear system operation, prior to 7,500 landings or within 500 landings after the effective date of this AD, whichever comes later, replace main gear actuating ram retaining ring P/N ACM18254 with a serviceable retaining ring having less than 7,500 landings in accordance with the F27 Structural Integrity Program under item 32-30-01, Revision 1, subitem d or in accordance with the Accomplishment Instructions of Fokker F27 Service Bulletin No. 32-136, dated February 18, 1980, or later FAA approved revisions. (Note: Established life limits are not to be exceeded.) F. Applies to airplane S/N 10505 to 10547 inclusive and 10550. To ensure proper function of the pitot static system, within the next 100 hours time in service, modify the pitot static system in accordance with the Fokker F27 Service Bulletin No. 34-41, dated March 13, 1978, or later FAA approved revisions. G. Applies to airplane S/N 10299 to 10547 inclusive. To prevent damage to the cable loom, within the next 200 hours time in service, inspect and modify as necessary the cable loom in accordance with Fokker F27 Service Bulletin No. 30-34 dated April 17, 1978, or later FAA approved revisions. H. Applies to airplane S/N 10526, 10527, 10529, 10543, 10547, 10533, 10555, 10556, 10563, 10564, 10565, 10570, 10582 and 10583. To ensure airplane battery power to the main DC tie bus, within 100 hours time in service, inspect and modify as necessary the battery wiring to the battery reverse current circuit breakers in accordance with the Fokker F27 Special Instructions No. 76 dated November 20, 1978, or later FAA approved revisions. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. Alternate means of compliance or other actions which provide an equivalent level of safety may be used when approved by the Chief, Seattle Area Aircraft Certification Office, FAA Northwest Region. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). This amendment becomes effective August 10, 1981. FOOTER:
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