AD 98-07-01
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | BAE Systems (Operations) Limited | ATP | Airworthiness Directives; British Aerospace BAe Model ATP Airplanes |
Unsafe Condition
Failure of the engine power cables could cause loss of function of the power control levers on the console and subsequent loss of normal control of engine power.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Perform a detailed visual inspection and tests for damage of the engine power cables in accordance with Jetstream Service Bulletin ATP-76-16. Replace any damaged cable with a new cable. The inspection must be repeated at intervals not exceeding 1,000 landings, unless modified to 5,000 landings by installing the pulley assembly modification per ATP-76-18.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Required as indicated, unless accomplished previously. The initial inspection must be done by the earlier of 1,000 total landings on the engine power cable or within 200 landings after the effective date of this AD, whichever occurs later, and within 75 days after the effective date. Replacement of damaged cables must be done prior to further flight.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
BAE Systems (Operations) Limited Model ATP airplanes, constructor's numbers 2002 through 2063 inclusive.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Inspect Engine Power Cables
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_98-07-01.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 98-07-01 Document Type: AD Final Rules Docket Number: 94-NM-212-AD Subject Heading: Airworthiness Directives; British Aerospace BAe Model ATP Airplanes Subject: Inspect Engine Power Cables Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 04/27/1998 Make: BAE Systems (Operations) Limited Model: ATP Product Type: Aircraft Product Subtype: Large Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 [63 FR 13776 NO. 55 03/23/98] Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 98-07-01 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 94-NM-212-AD AMENDMENT: 39-10419 AD NUMBER: 98-07-01 SUBJECT HEADING: Airworthiness Directives; British Aerospace BAe Model ATP Airplanes ACTION: Final rule SUMMARY: This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace BAe Model ATP airplanes, that requires inspections and tests for damage of the engine power cables, and replacement of any damaged cable with a new cable. This amendment also provides for optional modification of the engine power control cable pulley assembly. This amendment is prompted by a report of failure of an engine power cable, which could cause loss of function of the power control levers on the console. The actions specified by this AD are intended to prevent loss of function of the power control levers on the console, and subsequent loss of normal control of engine power. DATES: Effective April 27, 1998. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of April 27, 1998. ADDRESSES: The service information referenced in this AD may be obtained from AI(R) American Support, Inc., 13850 McLearen Road, Herndon, Virginia 20171. This information may be examined at the Federal Aviation Administration (FAA), Transport Airplane Directorate, Rules Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. FOR FURTHER INFORMATION CONTACT: Norman B. Martenson, Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 227-2110; fax (425) 227-1149. SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an airworthiness directive (AD) that is applicable to certain British Aerospace BAe Model ATP airplanes was published in the Federal Register on September 13, 1995 (60 FR 47501). That action proposed to require inspections and tests for damage of the engine power cables, and replacement of any damaged cable with a new cable. Comments Interested persons have been afforded an opportunity to participate in the making of this amendment. Due consideration has been given to the single comment received. The commenter supports the proposed rule. Actions Since Issuance of Proposal Since the issuance of the proposal, the manufacturer has issued British Aerospace Service Bulletin ATP-76-18, dated June 21, 1995, which describes procedures for the modification of the engine power control cable pulley assembly. The modification involves increasing the diameter of the pulley of the engine power control quadrant’s lower pulley group between stations 398FS to 408FS from 1.5 inches to 2.36 inches, and repositioning of the lower pulley group slightly forward and upward. The service bulletin specifies that, if accomplished, this modification would extend the fatigue life of the engine power control cables, and would allow the repetitive inspection interval to be increased from 1,000 landings to 5,000 landings. The Civil Aviation Authority (CAA), which is the airworthiness authority for the United Kingdom, classified this service bulletin as optional. The FAA has revised this final rule to add accomplishment of this modification as an option to permit extension of the repetitive inspection interval specified in this AD. Additionally, the cost impact information, below, has been revised to specify the number of work hours that would be required to accomplish the optional modification. Conclusion After careful review of the available data, including the comment noted above, the FAA has determined that air safety and the public interest require the adoption of the rule with the change previously described. The FAA has determined that this change will neither increase the economic burden on any operator nor increase the scope of the AD. Cost Impact The FAA estimates that 10 airplanes of U.S. registry will be affected by this AD, that it will take approximately 2 work hours per airplane to accomplish the required actions, and that the average labor rate is $60 per work hour. Based on these figures, the cost impact of the AD on U.S. operators is estimated to be $1,200, or $120 per airplane. The cost impact figure discussed above is based on assumptions that no operator has yet accomplished any of the requirements of this AD action, and that no operator would accomplish those actions in the future if this AD were not adopted. Should an operator elect to accomplish the optional modification provided by this AD, it would take approximately 80 work hours per airplane to accomplish it, at an average labor rate of $60 per work hour. Based on these figures, the cost impact of this optional modification is estimated to be $4,800 per airplane. Regulatory Impact The regulations adopted herein will not have substantial direct effects on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. Therefore, in accordance with Executive Order 12612, it is determined that this final rule does not have sufficient federalism implications to warrant the preparation of a Federalism Assessment. For the reasons discussed above, I certify that this action (1) is not a "significant regulatory action" under Executive Order 12866; (2) is not a "significant rule" under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. A final evaluation has been prepared for this action and it is contained in the Rules Docket. A copy of it may be obtained from the Rules Docket at the location provided under the caption "ADDRESSES." List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows: PART 39 - AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. Section 39.13 is amended by adding the following new airworthiness directive: REGULATORY TEXT: 98-07-01 BRITISH AEROSPACE REGIONAL AIRCRAFT [Formerly Jetstream Aircraft Limited, British Aerospace (Commercial Aircraft) Limited]: Amendment 39-10419. Docket 94-NM-212-AD. Applicability: BAe Model ATP airplanes, constructor's numbers 2002 through 2063 inclusive; certificated in any category. NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (d) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance: Required as indicated, unless accomplished previously. To prevent loss of function of the power control levers on the console, and subsequent loss of normal control of engine power due to failure of the engine power cables, accomplish the following: (a) Perform a detailed visual inspection and tests for damage of the engine power cables, in accordance with Jetstream Service Bulletin ATP-76-16, dated October 14, 1994, at the earlier of the times specified in paragraphs (a)(1) and (a)(2) of this AD. Thereafter repeat this inspection and tests at intervals not to exceed 1,000 landings. (1) Prior to the accumulation of 1,000 total landings on the engine power cable, or within 200 landings after the effective date of this AD, whichever occurs later. (2) Within 75 days after the effective date of this AD. (b) If any damaged engine power cable is found, prior to further flight, replace the damaged engine power cable with a new cable in accordance with Jetstream Service Bulletin ATP-76-16, dated October 14, 1994. Except as provided by paragraph (c) of this AD, repeat the inspection and tests required by paragraph (a) of this AD thereafter at intervals not to exceed 1,000 landings. (c) Modification of the engine power control cable pulley assembly in accordance with British Aerospace Service Bulletin ATP-76-18, dated June 21, 1995, allows the interval for accomplishment of the repetitive inspection and tests required by paragraph (a) of this AD to be increased to 5,000 landings. (d) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, International Branch, ANM-116. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the International Branch, ANM-116. (e) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (f) The inspection, tests, and replacement shall be done in accordance with Jetstream Service Bulletin ATP-76-16, dated October 14, 1994. The modification, if accomplished, shall be done in accordance with Jetstream Service Bulletin ATP-76-18, dated June 21, 1995. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from AI(R) American Support, Inc., 13850 McLearen Road, Herndon, Virginia 20171. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (g) This amendment becomes effective on April 27, 1998. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_98-07-01.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 98-07-01 Document Type: AD Final Rules Docket Number: 94-NM-212-AD Subject Heading: Airworthiness Directives; British Aerospace BAe Model ATP Airplanes Subject: Inspect Engine Power Cables Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 04/27/1998 Make: BAE Systems (Operations) Limited Model: ATP 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 [63 FR 13776 NO. 55 03/23/98] Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 98-07-01 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 94-NM-212-AD AMENDMENT: 39-10419 AD NUMBER: 98-07-01 SUBJECT HEADING: Airworthiness Directives; British Aerospace BAe Model ATP Airplanes ACTION: Final rule SUMMARY: This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace BAe Model ATP airplanes, that requires inspections and tests for damage of the engine power cables, and replacement of any damaged cable with a new cable. This amendment also provides for optional modification of the engine power control cable pulley assembly. This amendment is prompted by a report of failure of an engine power cable, which could cause loss of function of the power control levers on the console. The actions specified by this AD are intended to prevent loss of function of the power control levers on the console, and subsequent loss of normal control of engine power. DATES: Effective April 27, 1998. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of April 27, 1998. ADDRESSES: The service information referenced in this AD may be obtained from AI(R) American Support, Inc., 13850 McLearen Road, Herndon, Virginia 20171. This information may be examined at the Federal Aviation Administration (FAA), Transport Airplane Directorate, Rules Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. FOR FURTHER INFORMATION CONTACT: Norman B. Martenson, Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 227-2110; fax (425) 227-1149. SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an airworthiness directive (AD) that is applicable to certain British Aerospace BAe Model ATP airplanes was published in the Federal Register on September 13, 1995 (60 FR 47501). That action proposed to require inspections and tests for damage of the engine power cables, and replacement of any damaged cable with a new cable. Comments Interested persons have been afforded an opportunity to participate in the making of this amendment. Due consideration has been given to the single comment received. The commenter supports the proposed rule. Actions Since Issuance of Proposal Since the issuance of the proposal, the manufacturer has issued British Aerospace Service Bulletin ATP-76-18, dated June 21, 1995, which describes procedures for the modification of the engine power control cable pulley assembly. The modification involves increasing the diameter of the pulley of the engine power control quadrant’s lower pulley group between stations 398FS to 408FS from 1.5 inches to 2.36 inches, and repositioning of the lower pulley group slightly forward and upward. The service bulletin specifies that, if accomplished, this modification would extend the fatigue life of the engine power control cables, and would allow the repetitive inspection interval to be increased from 1,000 landings to 5,000 landings. The Civil Aviation Authority (CAA), which is the airworthiness authority for the United Kingdom, classified this service bulletin as optional. The FAA has revised this final rule to add accomplishment of this modification as an option to permit extension of the repetitive inspection interval specified in this AD. Additionally, the cost impact information, below, has been revised to specify the number of work hours that would be required to accomplish the optional modification. Conclusion After careful review of the available data, including the comment noted above, the FAA has determined that air safety and the public interest require the adoption of the rule with the change previously described. The FAA has determined that this change will neither increase the economic burden on any operator nor increase the scope of the AD. Cost Impact The FAA estimates that 10 airplanes of U.S. registry will be affected by this AD, that it will take approximately 2 work hours per airplane to accomplish the required actions, and that the average labor rate is $60 per work hour. Based on these figures, the cost impact of the AD on U.S. operators is estimated to be $1,200, or $120 per airplane. The cost impact figure discussed above is based on assumptions that no operator has yet accomplished any of the requirements of this AD action, and that no operator would accomplish those actions in the future if this AD were not adopted. Should an operator elect to accomplish the optional modification provided by this AD, it would take approximately 80 work hours per airplane to accomplish it, at an average labor rate of $60 per work hour. Based on these figures, the cost impact of this optional modification is estimated to be $4,800 per airplane. Regulatory Impact The regulations adopted herein will not have substantial direct effects on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. Therefore, in accordance with Executive Order 12612, it is determined that this final rule does not have sufficient federalism implications to warrant the preparation of a Federalism Assessment. For the reasons discussed above, I certify that this action (1) is not a "significant regulatory action" under Executive Order 12866; (2) is not a "significant rule" under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. A final evaluation has been prepared for this action and it is contained in the Rules Docket. A copy of it may be obtained from the Rules Docket at the location provided under the caption "ADDRESSES." List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows: PART 39 - AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. Section 39.13 is amended by adding the following new airworthiness directive: REGULATORY TEXT: 98-07-01 BRITISH AEROSPACE REGIONAL AIRCRAFT [Formerly Jetstream Aircraft Limited, British Aerospace (Commercial Aircraft) Limited]: Amendment 39-10419. Docket 94-NM-212-AD. Applicability: BAe Model ATP airplanes, constructor's numbers 2002 through 2063 inclusive; certificated in any category. NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (d) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance: Required as indicated, unless accomplished previously. To prevent loss of function of the power control levers on the console, and subsequent loss of normal control of engine power due to failure of the engine power cables, accomplish the following: (a) Perform a detailed visual inspection and tests for damage of the engine power cables, in accordance with Jetstream Service Bulletin ATP-76-16, dated October 14, 1994, at the earlier of the times specified in paragraphs (a)(1) and (a)(2) of this AD. Thereafter repeat this inspection and tests at intervals not to exceed 1,000 landings. (1) Prior to the accumulation of 1,000 total landings on the engine power cable, or within 200 landings after the effective date of this AD, whichever occurs later. (2) Within 75 days after the effective date of this AD. (b) If any damaged engine power cable is found, prior to further flight, replace the damaged engine power cable with a new cable in accordance with Jetstream Service Bulletin ATP-76-16, dated October 14, 1994. Except as provided by paragraph (c) of this AD, repeat the inspection and tests required by paragraph (a) of this AD thereafter at intervals not to exceed 1,000 landings. (c) Modification of the engine power control cable pulley assembly in accordance with British Aerospace Service Bulletin ATP-76-18, dated June 21, 1995, allows the interval for accomplishment of the repetitive inspection and tests required by paragraph (a) of this AD to be increased to 5,000 landings. (d) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, International Branch, ANM-116. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the International Branch, ANM-116. (e) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (f) The inspection, tests, and replacement shall be done in accordance with Jetstream Service Bulletin ATP-76-16, dated October 14, 1994. The modification, if accomplished, shall be done in accordance with Jetstream Service Bulletin ATP-76-18, dated June 21, 1995. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from AI(R) American Support, Inc., 13850 McLearen Road, Herndon, Virginia 20171. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (g) This amendment becomes effective on April 27, 1998. FOOTER:
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