Airworthiness Directives; Bell Helicopter Textron Canada Helicopters, 42421-42424 [2012-17561]

Download as PDF Federal Register / Vol. 77, No. 139 / Thursday, July 19, 2012 / Rules and Regulations send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in the Related Information section of this AD. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. [FR Doc. 2012–17592 Filed 7–18–12; 8:45 am] that AD, Bell has learned that additional servos may need repair or removal. This AD expands the scope of the current AD to include inspections for all servos, and requires that servos meeting inspection requirements be marked with the letter ‘‘V’’ after the part number on the data plate. The actions are intended to detect any loose or misaligned parts in the servo that could lead to failure of the servo and subsequent loss of helicopter control. DATES: This AD becomes effective August 3, 2012. We must receive comments on this AD by September 17, 2012. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Docket: Go to https://www.regulations.gov. Follow the online instructions for sending your comments electronically. • Fax: 202–493–2251. • Mail: Send comments to the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590–0001. • Hand Delivery: Deliver to the ‘‘Mail’’ address between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. BILLING CODE 4910–13–P Examining The AD Docket (k) Related Information For more information about this AD, contact: (1) Non-Pilatus aircraft-related: Albert Ma, Aerospace Engineer, Wichita Aircraft Certification Office, FAA, 1801 S. Airport Road, Room 100, Wichita, Kansas 67209; phone: (316) 946–4151; fax: (316) 946–4107; email: albert.ma@faa.gov; or (2) Pilatus aircraft-related: Doug Rudolph, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329– 4059; fax: (816) 329–4090; email: doug. rudolph@faa.gov. (l) Material Incorporated by Reference None. Issued in Kansas City, Missouri, on July 13, 2012. Earl Lawrence, Manager, Small Airplane Directorate, Aircraft Certification Service. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2012–0716; Directorate Identifier 2012–SW–011–AD; Amendment 39–17121; AD 2012–14–07] RIN 2120–AA64 Airworthiness Directives; Bell Helicopter Textron Canada Helicopters Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. AGENCY: We are adopting an airworthiness directive (AD) superseding an existing airworthiness directive for Bell Helicopter Textron Canada (Bell) Model 407 and 427 helicopters. The existing AD requires inspecting certain hydraulic servo actuators (servo) to determine whether the shaft turns independently of the nut or the clevis assembly, and additional actions based upon the inspection’s outcome. The AD also requires reidentifying the servo. Since we issued tkelley on DSK3SPTVN1PROD with RULES SUMMARY: VerDate Mar<15>2010 16:56 Jul 18, 2012 Jkt 226001 You may examine the AD docket on the Internet at https://www.regulations. gov or in person at the Docket Operations Office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the economic evaluation, any comments received, and other information. The street address for the Docket Operations Office (telephone 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. For service information identified in this AD, contact contact Bell Helicopter Textron Canada Limited, 12,800 Rue de l’Avenir, Mirabel, Quebec J7J1R4; telephone (450) 437–2862 or (800) 363– 8023; fax (450) 433–0272; or at https:// www.bellcustomer.com/files/. You may review the referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. FOR FURTHER INFORMATION CONTACT: Matt Wilbanks, Aviation Safety Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222–5110; email matt.wilbanks@faa.gov. SUPPLEMENTARY INFORMATION: PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 42421 Comments Invited This AD is a final rule that involves requirements affecting flight safety, and we did not provide you with notice and an opportunity to provide your comments prior to it becoming effective. However, we invite you to participate in this rulemaking by submitting written comments, data, or views. We also invite comments relating to the economic, environmental, energy, or federalism impacts that resulted from adopting this AD. The most helpful comments reference a specific portion of the AD, explain the reason for any recommended change, and include supporting data. To ensure the docket does not contain duplicate comments, commenters should send only one copy of written comments, or if comments are filed electronically, commenters should submit them only one time. We will file in the docket all comments that we receive, as well as a report summarizing each substantive public contact with FAA personnel concerning this rulemaking during the comment period. We will consider all the comments we receive and may conduct additional rulemaking based on those comments. Discussion On September 19, 2011, we issued AD 2011–15–51, Amendment 39–16817 (76 FR 66609, October 27, 2011) for Bell Model 407 helicopters with a servo, part number (P/N) 206–076–062–105 or 206– 076–062–107, and Bell Model 427 helicopters, with a servo, P/N 206–076– 062–109 or 206–076–062–111, installed. This AD requires inspecting certain servos to determine whether the shaft turns independently of the nut or the clevis assembly. If the shaft turns independently, this AD requires replacing the servo with an airworthy servo. If the shaft does not turn independently, the AD requires inspecting to determine the condition of the lock washers. Based on the condition of the lock washers, the AD requires either replacing the servo with an airworthy servo or bending the tab of the lock washer flush against a flat surface of the nut or clevis assembly. The AD also requires reidentifying the servo by metal-impression stamping or vibro-etching ‘‘67–01’’ onto the modification plate. The AD was prompted by a report that a supplier had a ‘‘quality escape’’ resulting in servos with a loose nut, shaft, and clevis assembly because of improper lockwasher installation. An investigation after an accident revealed the clevis nut on the servo was loose. Transport Canada, which is the aviation authority for Canada, notified the FAA of this E:\FR\FM\19JYR1.SGM 19JYR1 42422 Federal Register / Vol. 77, No. 139 / Thursday, July 19, 2012 / Rules and Regulations unsafe condition and issued AD No. CF–2011–17, dated June 30, 2011. The actions specified by AD 2011–15–51 are intended to prevent a malfunction of a servo in the flight control system and subsequent loss of helicopter control. Actions Since Existing AD Was Issued Since we issued AD 2011–15–51 (76 FR 66609, October 27, 2011), Transport Canada issued AD No. CF–2011–17R1, dated December 19, 2011 (AD CF–2011– 17R1), which supersedes AD CF–2011– 17, to correct an unsafe condition for the Bell Model 407, serial numbers 53000 through 53900, 53911 through 53999, and 54000 through 54081, equipped with servos, P/N 206–076–062–105 or P/N 206–076–062–107; and Model 427 helicopters, serial numbers 56001 through 56077, 58001 and 58002, equipped with servos, P/N 206–076– 062–109 or P/N 206–076–062–111. Transport Canada advises that additional servos may have a loose nut, shaft, and clevis assembly after the supplier’s ‘‘quality escape.’’ Therefore, Transport Canada revised its original AD to include all installed servos, and to require that servos already inspected according to its original AD be reidentified with the letter ‘‘V’’ at the end of the part number on the data plate. FAA’s Determination These helicopters have been approved by the aviation authority of Canada and are approved for operation in the United States. Pursuant to our bilateral agreement with Canada, Transport Canada, its technical representative, has notified us of the unsafe condition described in its AD. We are issuing this AD because we evaluated all information provided by Transport Canada and determined the unsafe condition exists and is likely to exist or develop on other helicopters of these same type designs. tkelley on DSK3SPTVN1PROD with RULES Related Service Information We reviewed Bell Alert Service Bulletin (ASB) 407–11–96, Revision B, for the Model 407 helicopter, and Bell ASB 427–11–35, Revision B, for the Model 427 helicopter. Both ASBs are dated August 29, 2011 and describe procedures for performing a one-time inspection of the servos before further flight, and reidentifying servos that meet all of the inspection requirements. Transport Canada classified this service information as mandatory and issued AD No. CF–2011–17R1 to ensure the continued airworthiness of these helicopters. VerDate Mar<15>2010 16:56 Jul 18, 2012 Jkt 226001 AD Requirements This AD retains the inspection requirements of AD 2011–15–51 (76 FR 66609, October 27, 2011), and adds a requirement to mark the letter ‘‘V’’ at the end of the part number on the data plate if the servo meets all of the inspection’s requirements. This AD also expands the applicability to all servos. Costs of Compliance We estimate that this AD will affect 582 helicopters of U.S. Registry and that labor costs will average $85 a work hour. Based on these estimates, we expect the following costs: • The required inspection will take about a 1⁄2 hour for a labor cost of about $43 per helicopter. The cost for the total U.S. fleet would be $25,026. • Replacing the servo, if needed, will require 2 work hours for a labor cost of $170. Parts will cost $33,000 for a total cost of $33,170 per helicopter. FAA’s Justification and Determination of the Effective Date Providing an opportunity for public comments before adopting these AD requirements would delay implementing the safety actions needed to detect any loose or misaligned parts in the servo, the failure of which could adversely affect control of the helicopter. Therefore, we find that the risk to the flying public justifies waiving notice and comment prior to adoption of this rule because the required corrective actions must be accomplished before further flight. 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. Regulatory Findings We determined that this AD will not have federalism implications under PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 Executive Order 13132. This AD 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. For the reasons discussed, I certify that this AD: 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); 3. Will not affect intrastate aviation in Alaska to the extent that it justifies making a regulatory distinction; and 4. 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. We prepared an economic evaluation of the estimated costs to comply with this AD and placed it in the AD docket. 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 FAA amends 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. The FAA amends § 39.13 by removing Amendment 39–16817 (76 FR 66609, October 27, 2011), and adding the following new airworthiness directive (AD): ■ 2012–14–07 Bell Helicopter Textron Canada Helicopters: Amendment 39– 17121; Docket No. FAA–2012–0716; Directorate Identifier 2012–SW–011–AD. (a) Applicability This AD applies to the following helicopters, certificated in any category: (1) Model 407 helicopters, serial numbers (S/Ns) 53000 through 53900, 53911 through 53999, and 54000 through 54081, with a hydraulic servo actuator assembly (servo) part number (P/N) 206–076–062–105 or P/N 206–076–062–107; and (2) Model 427 helicopters, S/Ns 56001 through 56077, 58001, and 58002, with a servo, P/N 206–076–062–109 or P/N 206– 076–062–111. (b) Unsafe Condition This AD defines the unsafe condition as a loose or misaligned part in the servo that E:\FR\FM\19JYR1.SGM 19JYR1 Federal Register / Vol. 77, No. 139 / Thursday, July 19, 2012 / Rules and Regulations This AD supersedes AD 2011–15–51, Amendment 39–16817 (76 FR 66609, October 27, 2011). (e) Compliance You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time. (ii) Applying only hand pressure, determine whether the nut, the shaft, or the clevis assembly, depicted as items 225, 215 and 205, respectively, in Figure 1 to Paragraph (f) of this AD, turn independently. If the shaft turns independently of the nut or clevis assembly, before further flight, replace the servo with an airworthy servo. (iii) If the shaft does not turn independently, inspect to determine if at VerDate Mar<15>2010 16:56 Jul 18, 2012 Jkt 226001 PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 (f) Required Actions (1) Before further flight, conduct a one-time visual inspection of the servo by doing the following: (i) Retract the boot depicted as 230 in Figure 1 to Paragraph (f) of this AD. least one tab of the lock washer is bent flush against a flat surface of the nut and if at least one tab of the lock washer is bent flush against a flat surface of the clevis assembly. E:\FR\FM\19JYR1.SGM 19JYR1 ER19JY12.000</GPH> (d) Effective Date This AD becomes effective August 3, 2012. (c) Other Affected ADs tkelley on DSK3SPTVN1PROD with RULES could lead to failure of the servo and subsequent loss of helicopter control. 42423 42424 Federal Register / Vol. 77, No. 139 / Thursday, July 19, 2012 / Rules and Regulations (iv) If at least one lock washer tab is not aligned and bent flush with a nut flat surface and at least one lock washer tab is not aligned and bent flush with a flat surface of the clevis assembly, before further flight, replace the servo with an airworthy servo. (v) If any tab of the lock washer is not bent flush against either a flat surface of the nut or clevis assembly, bend the tab flush against a flat surface. (2) After accomplishing paragraphs (f)(1)(i) through (f)(1)(v), vibro-etch the letter ‘‘V’’ at the end of the part number on the data plate. DEPARTMENT OF TRANSPORTATION (g) Alternative Methods of Compliance (AMOCs) AGENCY: (1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Matt Wilbanks, Aviation Safety Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222–5110; email matt.wilbanks@faa.gov. (2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office before operating any aircraft complying with this AD through an AMOC. (h) Additional Information (1) Bell Helicopter Alert Service Bulletins 407–11–96 and 427–11–35, both Revision B and both dated August 29, 2011, which are not incorporated by reference, contain additional information about the subject of this AD. For service information identified in this AD, contact Bell Helicopter Textron Canada Limited, 12,800 Rue de l’Avenir, Mirabel, Quebec J7J1R4; telephone (450) 437–2862 or (800) 363–8023; fax (450) 433– 0272; or at https://www.bellcustomer.com/ files/. You may review a copy of the service information at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. (2) The subject of this AD is addressed in Transport Canada AD CF–2011–17R1, dated December 19, 2011. (i) Subject 14 CFR Part 39 [Docket No. FAA–2010–1095; Directorate Identifier 2009–NE–40–AD; Amendment 39– 17104; AD 2012–13–02] RIN 2120–AA64 Airworthiness Directives; Pratt & Whitney Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule. We are superseding an existing airworthiness directive (AD) for all Pratt & Whitney Division PW4074 and PW4077 turbofan engines. That AD currently requires removing the 15th stage high-pressure compressor (HPC) disk within 12,000 cycles since new (CSN) or using a drawdown removal plan for disks that exceed 12,000 CSN. This new AD requires the same actions and clarifies that 15th stage HPC disks that have accumulated more than 9,865 CSN require a borescope inspection (BSI) or eddy current inspection (ECI) of the disk outer rim front rail for cracks prior to accumulating 12,000 CSN. This AD was prompted by a request from an operator that we clarify our inspection schedule for 15th stage HPC disks that have accumulated more than 9,865, but less than 12,000 CSN, on the effective date of the AD. We are issuing this AD to prevent cracks from propagating into the disk bolt holes, which could result in a failure of the 15th stage HPC disk, uncontained engine failure, and damage to the airplane. DATES: This AD is effective August 23, 2012. The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of September 8, 2011 (76 FR 47056, August 4, 2011). ADDRESSES: For service information identified in this AD, contact Pratt & Whitney, 400 Main St., East Hartford, CT 06108; phone: 860–565–7700; fax: 860–565–1605. You may review copies of the referenced service information at the FAA, Engine & Propeller Directorate, 16 New England Executive Park, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7125. SUMMARY: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2011–14–07, Amendment 39–16742 (76 FR 47056, August 4, 2011). That AD applies to the specified products. The NPRM published in the Federal Register on February 24, 2012 (77 FR 11017). That NPRM proposed to continue to require removing the 15th stage HPC disk within 12,000 CSN or using a drawdown removal plan for disks that exceed 12,000 CSN. That NPRM also proposed to clarify our inspection schedule for 15th stage HPC disks that have accumulated more than 9,865, but less than 12,000 CSN, on the effective date of the AD. Comments We gave the public the opportunity to participate in developing this AD. We have considered the comments received. United Airlines and The Boeing Company support the NPRM. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting the AD as proposed. Examining the AD Docket Issued in Fort Worth, Texas, on July 2, 2012. Kim Smith, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2012–17561 Filed 7–18–12; 8:45 am] BILLING CODE 4910–13–P VerDate Mar<15>2010 16:56 Jul 18, 2012 Jkt 226001 Costs of Compliance We estimate that this AD will affect 44 engines installed on airplanes of U.S. registry. Prorated parts life will cost about $66,000 per 15th stage HPC disk. Based on these figures, we estimate the total cost of the AD to U.S. operators to be $2,904,000. The new requirements of this AD add no additional economic burden. You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Management Facility between Joint Aircraft Service Component (JASC) Code: 6730, Rotorcraft Servo System. tkelley on DSK3SPTVN1PROD with RULES Federal Aviation Administration 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800–647–5527) is Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Ian Dargin, Aerospace Engineer, Engine Certification Office, FAA, 12 New England Executive Park, Burlington, MA 01803; phone: 781–238–7178; fax: 781– 238–7199; email: ian.dargin@faa.gov. SUPPLEMENTARY INFORMATION: Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 E:\FR\FM\19JYR1.SGM 19JYR1

Agencies

[Federal Register Volume 77, Number 139 (Thursday, July 19, 2012)]
[Rules and Regulations]
[Pages 42421-42424]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-17561]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0716; Directorate Identifier 2012-SW-011-AD; 
Amendment 39-17121; AD 2012-14-07]
RIN 2120-AA64


Airworthiness Directives; Bell Helicopter Textron Canada 
Helicopters

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule; request for comments.

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

SUMMARY: We are adopting an airworthiness directive (AD) superseding an 
existing airworthiness directive for Bell Helicopter Textron Canada 
(Bell) Model 407 and 427 helicopters. The existing AD requires 
inspecting certain hydraulic servo actuators (servo) to determine 
whether the shaft turns independently of the nut or the clevis 
assembly, and additional actions based upon the inspection's outcome. 
The AD also requires reidentifying the servo. Since we issued that AD, 
Bell has learned that additional servos may need repair or removal. 
This AD expands the scope of the current AD to include inspections for 
all servos, and requires that servos meeting inspection requirements be 
marked with the letter ``V'' after the part number on the data plate. 
The actions are intended to detect any loose or misaligned parts in the 
servo that could lead to failure of the servo and subsequent loss of 
helicopter control.

DATES: This AD becomes effective August 3, 2012.
    We must receive comments on this AD by September 17, 2012.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Docket: Go to https://www.regulations.gov. Follow the online instructions for sending your 
comments electronically.
     Fax: 202-493-2251.
     Mail: Send comments to the U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590-0001.
     Hand Delivery: Deliver to the ``Mail'' address between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.

Examining The AD Docket

    You may examine the AD docket on the Internet at https://www.regulations.gov or in person at the Docket Operations Office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this AD, the economic evaluation, any 
comments received, and other information. The street address for the 
Docket Operations Office (telephone 800-647-5527) is in the ADDRESSES 
section. Comments will be available in the AD docket shortly after 
receipt.
    For service information identified in this AD, contact contact Bell 
Helicopter Textron Canada Limited, 12,800 Rue de l'Avenir, Mirabel, 
Quebec J7J1R4; telephone (450) 437-2862 or (800) 363-8023; fax (450) 
433-0272; or at https://www.bellcustomer.com/files/. You may review the 
referenced service information at the FAA, Office of the Regional 
Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, 
Texas 76137.

FOR FURTHER INFORMATION CONTACT: Matt Wilbanks, Aviation Safety 
Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 
2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-5110; 
email matt.wilbanks@faa.gov.

SUPPLEMENTARY INFORMATION:

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not provide you with notice and an opportunity to 
provide your comments prior to it becoming effective. However, we 
invite you to participate in this rulemaking by submitting written 
comments, data, or views. We also invite comments relating to the 
economic, environmental, energy, or federalism impacts that resulted 
from adopting this AD. The most helpful comments reference a specific 
portion of the AD, explain the reason for any recommended change, and 
include supporting data. To ensure the docket does not contain 
duplicate comments, commenters should send only one copy of written 
comments, or if comments are filed electronically, commenters should 
submit them only one time. We will file in the docket all comments that 
we receive, as well as a report summarizing each substantive public 
contact with FAA personnel concerning this rulemaking during the 
comment period. We will consider all the comments we receive and may 
conduct additional rulemaking based on those comments.

Discussion

    On September 19, 2011, we issued AD 2011-15-51, Amendment 39-16817 
(76 FR 66609, October 27, 2011) for Bell Model 407 helicopters with a 
servo, part number (P/N) 206-076-062-105 or 206-076-062-107, and Bell 
Model 427 helicopters, with a servo, P/N 206-076-062-109 or 206-076-
062-111, installed. This AD requires inspecting certain servos to 
determine whether the shaft turns independently of the nut or the 
clevis assembly. If the shaft turns independently, this AD requires 
replacing the servo with an airworthy servo. If the shaft does not turn 
independently, the AD requires inspecting to determine the condition of 
the lock washers. Based on the condition of the lock washers, the AD 
requires either replacing the servo with an airworthy servo or bending 
the tab of the lock washer flush against a flat surface of the nut or 
clevis assembly. The AD also requires reidentifying the servo by metal-
impression stamping or vibro-etching ``67-01'' onto the modification 
plate. The AD was prompted by a report that a supplier had a ``quality 
escape'' resulting in servos with a loose nut, shaft, and clevis 
assembly because of improper lock-washer installation. An investigation 
after an accident revealed the clevis nut on the servo was loose. 
Transport Canada, which is the aviation authority for Canada, notified 
the FAA of this

[[Page 42422]]

unsafe condition and issued AD No. CF-2011-17, dated June 30, 2011. The 
actions specified by AD 2011-15-51 are intended to prevent a 
malfunction of a servo in the flight control system and subsequent loss 
of helicopter control.

Actions Since Existing AD Was Issued

    Since we issued AD 2011-15-51 (76 FR 66609, October 27, 2011), 
Transport Canada issued AD No. CF-2011-17R1, dated December 19, 2011 
(AD CF-2011-17R1), which supersedes AD CF-2011-17, to correct an unsafe 
condition for the Bell Model 407, serial numbers 53000 through 53900, 
53911 through 53999, and 54000 through 54081, equipped with servos, P/N 
206-076-062-105 or P/N 206-076-062-107; and Model 427 helicopters, 
serial numbers 56001 through 56077, 58001 and 58002, equipped with 
servos, P/N 206-076-062-109 or P/N 206-076-062-111. Transport Canada 
advises that additional servos may have a loose nut, shaft, and clevis 
assembly after the supplier's ``quality escape.'' Therefore, Transport 
Canada revised its original AD to include all installed servos, and to 
require that servos already inspected according to its original AD be 
reidentified with the letter ``V'' at the end of the part number on the 
data plate.

FAA's Determination

    These helicopters have been approved by the aviation authority of 
Canada and are approved for operation in the United States. Pursuant to 
our bilateral agreement with Canada, Transport Canada, its technical 
representative, has notified us of the unsafe condition described in 
its AD. We are issuing this AD because we evaluated all information 
provided by Transport Canada and determined the unsafe condition exists 
and is likely to exist or develop on other helicopters of these same 
type designs.

Related Service Information

    We reviewed Bell Alert Service Bulletin (ASB) 407-11-96, Revision 
B, for the Model 407 helicopter, and Bell ASB 427-11-35, Revision B, 
for the Model 427 helicopter. Both ASBs are dated August 29, 2011 and 
describe procedures for performing a one-time inspection of the servos 
before further flight, and reidentifying servos that meet all of the 
inspection requirements. Transport Canada classified this service 
information as mandatory and issued AD No. CF-2011-17R1 to ensure the 
continued airworthiness of these helicopters.

AD Requirements

    This AD retains the inspection requirements of AD 2011-15-51 (76 FR 
66609, October 27, 2011), and adds a requirement to mark the letter 
``V'' at the end of the part number on the data plate if the servo 
meets all of the inspection's requirements. This AD also expands the 
applicability to all servos.

Costs of Compliance

    We estimate that this AD will affect 582 helicopters of U.S. 
Registry and that labor costs will average $85 a work hour. Based on 
these estimates, we expect the following costs:
     The required inspection will take about a \1/2\ hour for a 
labor cost of about $43 per helicopter. The cost for the total U.S. 
fleet would be $25,026.
     Replacing the servo, if needed, will require 2 work hours 
for a labor cost of $170. Parts will cost $33,000 for a total cost of 
$33,170 per helicopter.

FAA's Justification and Determination of the Effective Date

    Providing an opportunity for public comments before adopting these 
AD requirements would delay implementing the safety actions needed to 
detect any loose or misaligned parts in the servo, the failure of which 
could adversely affect control of the helicopter. Therefore, we find 
that the risk to the flying public justifies waiving notice and comment 
prior to adoption of this rule because the required corrective actions 
must be accomplished before further flight.

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.

Regulatory Findings

    We determined that this AD will not have federalism implications 
under Executive Order 13132. This AD 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.
    For the reasons discussed, I certify that this AD:
    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);
    3. Will not affect intrastate aviation in Alaska to the extent that 
it justifies making a regulatory distinction; and
    4. 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.
    We prepared an economic evaluation of the estimated costs to comply 
with this AD and placed it in the AD docket.

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 FAA amends 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. The FAA amends Sec.  39.13 by removing Amendment 39-16817 (76 FR 
66609, October 27, 2011), and adding the following new airworthiness 
directive (AD):

2012-14-07 Bell Helicopter Textron Canada Helicopters: Amendment 39-
17121; Docket No. FAA-2012-0716; Directorate Identifier 2012-SW-011-
AD.

(a) Applicability

    This AD applies to the following helicopters, certificated in 
any category:
    (1) Model 407 helicopters, serial numbers (S/Ns) 53000 through 
53900, 53911 through 53999, and 54000 through 54081, with a 
hydraulic servo actuator assembly (servo) part number (P/N) 206-076-
062-105 or P/N 206-076-062-107; and
    (2) Model 427 helicopters, S/Ns 56001 through 56077, 58001, and 
58002, with a servo, P/N 206-076-062-109 or P/N 206-076-062-111.

(b) Unsafe Condition

    This AD defines the unsafe condition as a loose or misaligned 
part in the servo that

[[Page 42423]]

could lead to failure of the servo and subsequent loss of helicopter 
control.

(c) Other Affected ADs

    This AD supersedes AD 2011-15-51, Amendment 39-16817 (76 FR 
66609, October 27, 2011).

(d) Effective Date

    This AD becomes effective August 3, 2012.

(e) Compliance

    You are responsible for performing each action required by this 
AD within the specified compliance time unless it has already been 
accomplished prior to that time.

(f) Required Actions

    (1) Before further flight, conduct a one-time visual inspection 
of the servo by doing the following:
    (i) Retract the boot depicted as 230 in Figure 1 to Paragraph 
(f) of this AD.
[GRAPHIC] [TIFF OMITTED] TR19JY12.000

    (ii) Applying only hand pressure, determine whether the nut, the 
shaft, or the clevis assembly, depicted as items 225, 215 and 205, 
respectively, in Figure 1 to Paragraph (f) of this AD, turn 
independently. If the shaft turns independently of the nut or clevis 
assembly, before further flight, replace the servo with an airworthy 
servo.
    (iii) If the shaft does not turn independently, inspect to 
determine if at least one tab of the lock washer is bent flush 
against a flat surface of the nut and if at least one tab of the 
lock washer is bent flush against a flat surface of the clevis 
assembly.

[[Page 42424]]

    (iv) If at least one lock washer tab is not aligned and bent 
flush with a nut flat surface and at least one lock washer tab is 
not aligned and bent flush with a flat surface of the clevis 
assembly, before further flight, replace the servo with an airworthy 
servo.
    (v) If any tab of the lock washer is not bent flush against 
either a flat surface of the nut or clevis assembly, bend the tab 
flush against a flat surface.
    (2) After accomplishing paragraphs (f)(1)(i) through (f)(1)(v), 
vibro-etch the letter ``V'' at the end of the part number on the 
data plate.

(g) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Safety Management Group, FAA, may approve AMOCs 
for this AD. Send your proposal to: Matt Wilbanks, Aviation Safety 
Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 
2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-
5110; email matt.wilbanks@faa.gov.
    (2) For operations conducted under a 14 CFR part 119 operating 
certificate or under 14 CFR part 91, subpart K, we suggest that you 
notify your principal inspector, or lacking a principal inspector, 
the manager of the local flight standards district office or 
certificate holding district office before operating any aircraft 
complying with this AD through an AMOC.

(h) Additional Information

    (1) Bell Helicopter Alert Service Bulletins 407-11-96 and 427-
11-35, both Revision B and both dated August 29, 2011, which are not 
incorporated by reference, contain additional information about the 
subject of this AD. For service information identified in this AD, 
contact Bell Helicopter Textron Canada Limited, 12,800 Rue de 
l'Avenir, Mirabel, Quebec J7J1R4; telephone (450) 437-2862 or (800) 
363-8023; fax (450) 433-0272; or at https://www.bellcustomer.com/files/. You may review a copy of the service information at the FAA, 
Office of the Regional Counsel, Southwest Region, 2601 Meacham 
Blvd., Room 663, Fort Worth, Texas 76137.
    (2) The subject of this AD is addressed in Transport Canada AD 
CF-2011-17R1, dated December 19, 2011.

(i) Subject

    Joint Aircraft Service Component (JASC) Code: 6730, Rotorcraft 
Servo System.

    Issued in Fort Worth, Texas, on July 2, 2012.
Kim Smith,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2012-17561 Filed 7-18-12; 8:45 am]
BILLING CODE 4910-13-P
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