Airworthiness Directives; Bell Helicopter Textron Canada Model 407 Helicopters, 7016-7017 [05-2589]

Download as PDF 7016 Federal Register / Vol. 70, No. 27 / Thursday, February 10, 2005 / Rules and Regulations Related Information (l) Luftfhart Bundesamt airworthiness directive No. 2002–358/5, dated November 18, 2003, and Rolls-Royce Deutschland Ltd. & Co KG Service Bulletin No. TAY–73–1592, dated April 30, 2003 also address the subject of this AD. Issued in Burlington, Massachusetts, on February 1, 2005. Francis A. Favara, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 05–2370 Filed 2–9–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. 2004–SW–07–AD; Amendment 39–13963; AD 2005–03–07] RIN 2120–AA64 Airworthiness Directives; Bell Helicopter Textron Canada Model 407 Helicopters Federal Aviation Administration, DOT. ACTION: Final rule. AGENCY: SUMMARY: This amendment adopts a new airworthiness directive (AD) for Bell Helicopter Textron Canada (Bell) Model 407 helicopters that requires creating a component history card or equivalent record for each crosstube assembly, converting accumulated runon landings to an accumulated Retirement Index Number (RIN) count, and establishing a maximum accumulated RIN for certain crosstube assemblies. This amendment is prompted by fatigue testing, analysis, and evaluation by the manufacturer that determined that run-on landings impose a high stress on landing gear or crosstubes and may cause cracking in the area above the skid tube saddle. The actions specified by this AD are intended to prevent fatigue failure in a crosstube assembly due to excessive stress during run-on landings and subsequent loss of control of the helicopter. DATES: Effective March 17, 2005. FOR FURTHER INFORMATION CONTACT: Sharon Miles, Aviation Safety Engineer, FAA, Rotorcraft Directorate, Regulations and Policy Group, Fort Worth, Texas 76193–0111, telephone (817) 222–5122, fax (817) 222–5961. SUPPLEMENTARY INFORMATION: A proposal to amend 14 CFR part 39 to include an AD for the Bell Model 407 helicopters was published in the VerDate jul<14>2003 16:15 Feb 09, 2005 Jkt 205001 Federal Register on August 4, 2004 (69 FR 47041). That action proposed to require, before further flight, creating a component history card or equivalent record for each crosstube assembly, converting accumulated run-on landings to an accumulated RIN count, and establishing a retirement life of 5,000 accumulated RIN for the affected crosstube assemblies. Transport Canada, the airworthiness authority for Canada, notified the FAA that an unsafe condition may exist on Bell Model 407 helicopters. Transport Canada advises that run-on landings impose high stress on landing gear crosstubes, and to prevent possible crosstube failure, the manufacturer has introduced the life limitation of 5,000 RIN. Further evaluation has confirmed the possibility that an extensive training environment with run-on landings may impose high stress on crosstubes. The same condition may result from repetitive landings with forward travel with rotorcraft weight on the skids. Bell has issued Alert Service Bulletin No. 407–03–59, dated October 15, 2003, which specifies assigning a RIN count to forward and aft crosstube assemblies on Model 407 helicopters. Transport Canada classified this alert service bulletin as mandatory and issued AD No. CF–2004–03, dated February 11, 2004, to ensure the continued airworthiness of these helicopters in Canada. This helicopter model is manufactured in Canada and is type certificated for operation in the United States under the provisions of 14 CFR 21.29 and the applicable bilateral agreement. Pursuant to the applicable bilateral agreement, Transport Canada has kept the FAA informed of the situation described above. The FAA has examined the findings of Transport Canada reviewed all available information, and determined that AD action is necessary for products of this type design that are certificated for operation in the United States. Interested persons have been afforded an opportunity to participate in the making of this amendment. No comments were received on the proposal or the FAA’s determination of the cost to the public. The FAA has determined that air safety and the public interest require the adoption of the rule as proposed. The FAA estimates that this AD will affect 319 helicopters of U.S. registry and it will take approximately 4 work hours per helicopter to replace the forward and aft crosstube assemblies at an average labor rate of $65 per work hour. Required parts will cost approximately $6,670 per helicopter for PO 00000 Frm 00018 Fmt 4700 Sfmt 4700 both forward and aft low gear crosstube assemblies, or $8,450 per helicopter for both forward and aft high gear crosstube assemblies. Based on these figures, the total cost impact of this AD on U.S. operators is estimated to be $2,210,670 to replace the low gear crosstube assemblies on the entire fleet or $2,778,490 to replace the high-gear crosstube assemblies on the entire fleet and assuming the costs associated with creating and updating the historical component card are negligible. Regulatory Findings The regulations adopted herein will not have a substantial direct effect 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, it is determined that this final rule does not have federalism implications under Executive Order 13132. 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 economic 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 FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. E:\FR\FM\10FER1.SGM 10FER1 Federal Register / Vol. 70, No. 27 / Thursday, February 10, 2005 / Rules and Regulations List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, 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: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 for this AD, follow the procedures in 14 CFR 39.19. Contact the Regulations and Policy Group, Rotorcraft Directorate, FAA, for information about previously approved alternative methods of compliance. (f) This amendment becomes effective on March 17, 2005. Note 3: The subject of this AD is addressed in Transport Canada (Canada) AD No. CF– 2004–03, dated February 11, 2004. Issued in Fort Worth, Texas, on January 24, 2005. Mark R. Schilling, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 05–2589 Filed 2–9–05; 8:45 am] BILLING CODE 4910–13–P [Amended] 2. Section 39.13 is amended by adding a new airworthiness directive to read as follows: DEPARTMENT OF TRANSPORTATION 2005–03–07 Bell Helicopter Textron Canada (Bell): Amendment 39–13963. Docket No. 2004–SW–07–AD. Applicability: Model 407 helicopters, with landing gear crosstube assemblies, part number (P/N) 407–050–101–101 and –103; P/ N 407–050–102–101 and –103; P/N 407–050– 201–101 and –103; P/N 407–050–202–101 and –103; P/N 407–704–007–119; P/N 407– 722–101; P/N 407–723–104; P/N 407–724– 101; or P/N 407–725–104, installed, certificated in any category. Note 1: This AD applicability includes both Bell crosstube assemblies and Bell’s approved production and spare alternate crosstube assemblies from Aeronautical Accessories Incorporated (AAI). Compliance: Required as indicated, unless accomplished previously. To prevent fatigue failure of the crosstube assembly and subsequent loss of control of the helicopter, accomplish the following: (a) Before further flight, create a component history card or equivalent record for each crosstube assembly. (b) Before further flight, determine and record the accumulated Retirement Index Number (RIN) for each crosstube assembly as follows: (1) For each crosstube assembly, record one (1) RIN for every run-on landing. (2) For any crosstube assembly with an unknown number of run-on landings, assume and record ten (10) RINs for each 100 hours TIS since the crosstube assembly was installed (for example, 5,000 hours of timein-service equals 500 RIN). (c) Replace any crosstube assembly on or before reaching 5,000 RIN. Note 2: Bell Helicopter Textron Alert Service Bulletin No. 407–03–59, dated October 15, 2003, pertains to the subject of this AD. (d) This AD revises the Airworthiness Limitations section of the maintenance manual by establishing a retirement life of 5,000 RIN for the affected crosstube assemblies. (e) To request a different method of compliance or a different compliance time 14 CFR Part 39 I VerDate jul<14>2003 16:15 Feb 09, 2005 Jkt 205001 Federal Aviation Administration [Docket No. 2000–CE–38–AD; Amendment 39–13928; AD 2005–01–04] RIN 2120–AA64 Airworthiness Directives; Raytheon Aircraft Company 90, 99, 100, 200, and 300 Series Airplanes Federal Aviation Administration, DOT. ACTION: Final rule; correction. AGENCY: This document incorporates corrections to Airworthiness Directive (AD) 2005–01–04, which was published in the Federal Register on January 6, 2005 (70 FR 1169) with regulatory corrections published on January 27, 2005 (70 FR 3871). AD 2005–01–04 applies to certain Raytheon Aircraft Company 90, 99, 100, 200, and 300 series airplanes. This action incorporates the corrections into one document to help eliminate any confusion. We are re-issuing the AD in its entirety. EFFECTIVE DATE: The effective date of this AD remains February 22, 2005. ADDRESSES: To get the service information identified in this AD, contact Raytheon Aircraft Company, PO Box 85, Wichita, Kansas 67201–0085; telephone: (800) 625–7043. To review this service information, go to the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, go to: https:// www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html or call (202) 741– 6030. To view the AD docket, go to the Docket Management Facility; U.S. SUMMARY: PO 00000 Frm 00019 Fmt 4700 Sfmt 4700 7017 Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590– 001 or on the Internet at https:// dms.dot.gov. The docket number is FAA–2004–19089. FOR FURTHER INFORMATION CONTACT: Jeffrey A. Pretz, Aerospace Engineer, ACE–116W, 1801 Airport Road, Room 100, Wichita, Kansas 67209; telephone: (316) 946–4153; facsimile: (316) 946– 4407. SUPPLEMENTARY INFORMATION: Discussion On December 27, 2004, FAA issued AD 2005–01–04, Amendment 39–13928 (70 FR 1169, January 6, 2005), which applies to certain Raytheon Aircraft Company 90, 99, 100, 200, and 300 series airplanes. That AD requires you to check the airplane maintenance records from January 1, 1994, up to and including the effective date of that AD, for any MIL-H–6000B fuel hose replacements on the affected airplanes. On January 20, 2005, FAA made corrections to that AD through Federal Register publication (70 FR 3871). That AD correction changed the model number C90B in the applicability section to C90A. Need for This Action For clarity purposes, FAA is incorporating the original AD publication and the correction into one document to help eliminate any confusion. Consequently, we are reissuing the AD in its entirety. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under 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: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. FAA amends § 39.13 by removing Airworthiness Directive (AD) 98–15–13, Amendment 39–10664 (63 FR 38295–98, July 16, 1998), and by adding a new AD to read as follows: I 2005–01–04 Raytheon Aircraft Company: Amendment 39–13928; Docket No. E:\FR\FM\10FER1.SGM 10FER1

Agencies

[Federal Register Volume 70, Number 27 (Thursday, February 10, 2005)]
[Rules and Regulations]
[Pages 7016-7017]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-2589]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2004-SW-07-AD; Amendment 39-13963; AD 2005-03-07]
RIN 2120-AA64


Airworthiness Directives; Bell Helicopter Textron Canada Model 
407 Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: This amendment adopts a new airworthiness directive (AD) for 
Bell Helicopter Textron Canada (Bell) Model 407 helicopters that 
requires creating a component history card or equivalent record for 
each crosstube assembly, converting accumulated run-on landings to an 
accumulated Retirement Index Number (RIN) count, and establishing a 
maximum accumulated RIN for certain crosstube assemblies. This 
amendment is prompted by fatigue testing, analysis, and evaluation by 
the manufacturer that determined that run-on landings impose a high 
stress on landing gear or crosstubes and may cause cracking in the area 
above the skid tube saddle. The actions specified by this AD are 
intended to prevent fatigue failure in a crosstube assembly due to 
excessive stress during run-on landings and subsequent loss of control 
of the helicopter.

DATES: Effective March 17, 2005.

FOR FURTHER INFORMATION CONTACT: Sharon Miles, Aviation Safety 
Engineer, FAA, Rotorcraft Directorate, Regulations and Policy Group, 
Fort Worth, Texas 76193-0111, telephone (817) 222-5122, fax (817) 222-
5961.

SUPPLEMENTARY INFORMATION: A proposal to amend 14 CFR part 39 to 
include an AD for the Bell Model 407 helicopters was published in the 
Federal Register on August 4, 2004 (69 FR 47041). That action proposed 
to require, before further flight, creating a component history card or 
equivalent record for each crosstube assembly, converting accumulated 
run-on landings to an accumulated RIN count, and establishing a 
retirement life of 5,000 accumulated RIN for the affected crosstube 
assemblies.
    Transport Canada, the airworthiness authority for Canada, notified 
the FAA that an unsafe condition may exist on Bell Model 407 
helicopters. Transport Canada advises that run-on landings impose high 
stress on landing gear crosstubes, and to prevent possible crosstube 
failure, the manufacturer has introduced the life limitation of 5,000 
RIN. Further evaluation has confirmed the possibility that an extensive 
training environment with run-on landings may impose high stress on 
crosstubes. The same condition may result from repetitive landings with 
forward travel with rotorcraft weight on the skids.
    Bell has issued Alert Service Bulletin No. 407-03-59, dated October 
15, 2003, which specifies assigning a RIN count to forward and aft 
crosstube assemblies on Model 407 helicopters. Transport Canada 
classified this alert service bulletin as mandatory and issued AD No. 
CF-2004-03, dated February 11, 2004, to ensure the continued 
airworthiness of these helicopters in Canada.
    This helicopter model is manufactured in Canada and is type 
certificated for operation in the United States under the provisions of 
14 CFR 21.29 and the applicable bilateral agreement. Pursuant to the 
applicable bilateral agreement, Transport Canada has kept the FAA 
informed of the situation described above. The FAA has examined the 
findings of Transport Canada reviewed all available information, and 
determined that AD action is necessary for products of this type design 
that are certificated for operation in the United States.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were received on the 
proposal or the FAA's determination of the cost to the public. The FAA 
has determined that air safety and the public interest require the 
adoption of the rule as proposed.
    The FAA estimates that this AD will affect 319 helicopters of U.S. 
registry and it will take approximately 4 work hours per helicopter to 
replace the forward and aft crosstube assemblies at an average labor 
rate of $65 per work hour. Required parts will cost approximately 
$6,670 per helicopter for both forward and aft low gear crosstube 
assemblies, or $8,450 per helicopter for both forward and aft high gear 
crosstube assemblies. Based on these figures, the total cost impact of 
this AD on U.S. operators is estimated to be $2,210,670 to replace the 
low gear crosstube assemblies on the entire fleet or $2,778,490 to 
replace the high-gear crosstube assemblies on the entire fleet and 
assuming the costs associated with creating and updating the historical 
component card are negligible.

Regulatory Findings

    The regulations adopted herein will not have a substantial direct 
effect 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, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    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 economic 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 FAA, Office of the Regional 
Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, 
Texas.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, Section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

[[Page 7017]]

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

Adoption of the Amendment

0
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

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. Section 39.13 is amended by adding a new airworthiness directive to 
read as follows:

2005-03-07 Bell Helicopter Textron Canada (Bell): Amendment 39-
13963. Docket No. 2004-SW-07-AD.

    Applicability: Model 407 helicopters, with landing gear 
crosstube assemblies, part number (P/N) 407-050-101-101 and -103; P/
N 407-050-102-101 and -103; P/N 407-050-201-101 and -103; P/N 407-
050-202-101 and -103; P/N 407-704-007-119; P/N 407-722-101; P/N 407-
723-104; P/N 407-724-101; or P/N 407-725-104, installed, 
certificated in any category.

    Note 1: This AD applicability includes both Bell crosstube 
assemblies and Bell's approved production and spare alternate 
crosstube assemblies from Aeronautical Accessories Incorporated 
(AAI).

    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent fatigue failure of the crosstube assembly and 
subsequent loss of control of the helicopter, accomplish the 
following:
    (a) Before further flight, create a component history card or 
equivalent record for each crosstube assembly.
    (b) Before further flight, determine and record the accumulated 
Retirement Index Number (RIN) for each crosstube assembly as 
follows:
    (1) For each crosstube assembly, record one (1) RIN for every 
run-on landing.
    (2) For any crosstube assembly with an unknown number of run-on 
landings, assume and record ten (10) RINs for each 100 hours TIS 
since the crosstube assembly was installed (for example, 5,000 hours 
of time-in-service equals 500 RIN).
    (c) Replace any crosstube assembly on or before reaching 5,000 
RIN.

    Note 2: Bell Helicopter Textron Alert Service Bulletin No. 407-
03-59, dated October 15, 2003, pertains to the subject of this AD.

    (d) This AD revises the Airworthiness Limitations section of the 
maintenance manual by establishing a retirement life of 5,000 RIN 
for the affected crosstube assemblies.
    (e) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Contact the Regulations and Policy Group, Rotorcraft Directorate, 
FAA, for information about previously approved alternative methods 
of compliance.
    (f) This amendment becomes effective on March 17, 2005.

    Note 3: The subject of this AD is addressed in Transport Canada 
(Canada) AD No. CF-2004-03, dated February 11, 2004.


    Issued in Fort Worth, Texas, on January 24, 2005.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 05-2589 Filed 2-9-05; 8:45 am]
BILLING CODE 4910-13-P

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