Federal Register / Vol. 77, No. 102 / Friday, May 25, 2012 / Rules and Regulations 31169 

(g) Pivot Pin Replacement 

At the applicable time specified in 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Alert Service Bulletin 777–55A0018, 

Revision 1, dated March 6, 2012, except as 

required by paragraph (i) of this AD: Replace 

the pivot pins of the horizontal stabilizer 

with new or reworked pivot pins, including 

replacing the spacer with a new spacer or 

with one that has been determined to be 

without corrosion damage or other 

irregularities; in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 777–55A0018, Revision 1, 

dated March 6, 2012. 

(h) Repetitive Inspections 

At the applicable time specified in 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Alert Service Bulletin 777–55A0018, 

Revision 1, dated March 6, 2012: Do detailed 

inspections for cracks, corrosion damage, or 

other irregularity of the outer and inner pivot 

pins; and an ultrasonic inspection for 

cracking of the outer pivot pins; and do all 

applicable corrective actions; in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin 777–55A0018, 

Revision 1, dated March 6, 2012. Corrective 

actions must be done before further flight. 

Repeat the inspections at the applicable 

interval specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 777–55A0018, Revision 1, dated 

March 6, 2012. 

(i) Exception 

Where paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 777–55A0018, 

Revision 1, dated March 6, 2012, specifies a 

compliance time ‘‘after the Revision 1 date of 

this service bulletin,’’ this AD requires 

compliance within the specified compliance 

time ‘‘after the effective date of this AD.’’ 

(j) Credit for Previous Actions 

This paragraph provides credit for the 

actions specified in paragraphs (g) and (h) of 

this AD, if those actions were performed 

before the effective date of this AD using 

Boeing Alert Service Bulletin 777–55A0018, 

dated July 27, 2011. 

(k) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

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. 

Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. 

(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. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(l) Related Information 

For more information about this AD, 

contact James Sutherland, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

FAA, Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, Washington 

98057–3356; phone: 425–917–6533; fax: 425– 

917–6590; email: james.sutherland@faa.gov. 

(m) Material Incorporated by Reference 

You must use the following service 

information to do the actions required by this 

AD, unless the AD specifies otherwise. The 

Director of the Federal Register approved the 

incorporation by reference (IBR) of the 

following service information under 5 U.S.C. 

552(a) and 1 CFR part 51: 

(1) Boeing Alert Service Bulletin 777– 

55A0018, Revision 1, dated March 6, 2012. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, Washington 98124–2207; telephone 

206–544–5000, extension 1; fax 206–766– 

5680; email me.boecom@boeing.com; Internet 

https://www.myboeingfleet.com. 

(3) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

(4) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, call 202–741–6030, or go 

to: http://www.archives.gov/federal-register/ 

cfr/ibr-locations.html. 

Issued in Renton, Washington, on May 11, 

2012. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–12087 Filed 5–24–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0251; Directorate 

Identifier 2012–CE–002–AD; Amendment 

39–17058; AD 2012–10–09] 

RIN 2120–AA64 

Airworthiness Directives; Piper 

Aircraft, Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

certain Piper Aircraft, Inc. (type 

certificate previously held by The New 

Piper Aircraft Inc.) Models PA–31T and 

PA–31T1 airplanes. That AD currently 

requires correcting a model 

identification error on the aircraft data 

plate. Since we issued that AD, we have 

become aware that some owner/ 

operators of the affected airplanes 

modified the aircraft data plate in error 

because of confusion in the serial 

number applicability. Because of the 

confusion, the manufacturer has issued 

new service information to clarify 

affected airplane serial numbers. This 

new AD requires determining the 

airplane model based on the serial 

number and modifying the aircraft data 

plate to properly identify the airplane 

model. This new AD also requires doing 

a detailed search for all applicable 

airworthiness related documents that 

apply to any airplane that has an 

incorrectly marked data plate and take 

necessary corrective actions based on 

the search findings. We are issuing this 

AD to correct the unsafe condition on 

these products. 

DATES: This AD is effective June 29, 

2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of June 29, 2012. 

ADDRESSES: For service information 

identified in this AD, contact Piper 

Aircraft, Inc., 926 Piper Drive, Vero 

Beach, Florida 32960; telephone: (772) 

567–4361; Internet: www.piper.com. 

You may review copies of the 

referenced service information at the 

FAA, Small Airplane Directorate, 901 

Locust, Kansas City, Missouri 64106. 

For information on the availability of 

this material at the FAA, call (816) 329– 

4148. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility between 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. 


wreier-aviles on DSK5TPTVN1PROD with RULES
31170 Federal Register / Vol. 77, No. 102 / Friday, May 25, 2012 / Rules and Regulations 

FOR FURTHER INFORMATION CONTACT: 

Gregory ‘‘Keith’’ Noles, Aerospace 

Engineer, FAA, Atlanta Aircraft 

Certification Office, 1701 Columbia 

Avenue, College Park, Georgia 30337; 

phone: (404) 474–5551; fax: (404) 474– 

5606; email: gregory.noles@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 80–11–06, 

amendment 39–3776 (45 FR 35309, May 

27, 1980). That AD applies to the 

specified products. The NPRM 

published in the Federal Register on 

March 9, 2012 (77 FR 14316). The 

NPRM proposed to retain all 

requirements of AD 80–11–06, 

amendment 39–3776 (45 FR 35309, May 

27, 1980) and clarify the serial number 

applicability of the affected model 

airplanes. The NPRM also proposed to 

require a detailed search for all 

applicable airworthiness related 

documents that apply to any airplane 

that has an incorrectly marked aircraft 

data plate and take necessary corrective 

actions. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (77 

FR 14316, March 9, 2012) or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (77 FR 

14316, March 9, 2012) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (77 FR 14316, 

March 9, 2012). 

Costs of Compliance 

We estimate that this AD affects 158 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Inspect the aircraft data plate ........ 1 work-hour × $85 per hour = $85 Not applicable ................................ $85 $13,430 

We estimate the following costs to do 

any necessary modification and/or 

records search that will be required 

based on the results of the inspection. 

We have no way of determining the 

number of aircraft that might need 

modification: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Modify the aircraft data plate .............................. 1 work-hour × $85 per hour = $85 .... Not applicable .................................... $85 

Detailed search for all applicable airworthiness 

related documents that apply to any airplane 

that has an incorrectly marked aircraft data 

plate.

4 work-hours × $85 per hour = $340 Not applicable .................................... $340 

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 have 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 above, 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, 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. 

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 airworthiness directive (AD) 

80–11–06, amendment 39–3776 (45 FR 

35309, May 27, 1980), and adding the 

following new AD: 


wreier-aviles on DSK5TPTVN1PROD with RULES
Federal Register / Vol. 77, No. 102 / Friday, May 25, 2012 / Rules and Regulations 31171 

2012–10–09 Piper Aircraft, Inc. (Type 

Certificate Previously Held by The New 

Piper Aircraft Inc.): Amendment 39– 

17058; Docket No. FAA–2012–0251; 

Directorate Identifier 2012–CE–002–AD. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective June 29, 2012. 

(b) Affected ADs 

This AD supersedes AD 80–11–06, 

Amendment 39–3776 (45 FR 35309, May 27, 

1980). 

(c) Applicability 

This AD applies to the airplanes identified 

in paragraphs (c)(1) and (c)(2) of this AD, 

certificated in any category. 

(1) Model PA–31T airplanes, serial 

numbers 31T–7820001, 31T–7820002, 31T– 

7820003, 31T–7820004, 31T–7820005, 31T– 

7820006, 31T–7820007, 31T–7820008, 31T– 

7820009, 31T–7820010, 31T–7820011, 31T– 

7820012, 31T–7820013, 31T–7820014, 31T– 

7820015, 31T–7820016, 31T–7820017, 31T– 

7820018, 31T–7820019, 31T–7820020, 31T– 

7820021, 31T–7820022, 31T–7820023, 31T– 

7820024, 31T–7820025, 31T–7820026, 31T– 

7820027, 31T–7820028, 31T–7820029, 31T– 

7820030, 31T–7820031, 31T–7820032, 31T– 

7820033, 31T–7820034, 31T–7820035, 31T– 

7820036, 31T–7820037, 31T–7820038, 31T– 

7820039, 31T–7820040, 31T–7820041, 31T– 

7820042, 31T–7820043, 31T–7820044, 31T– 

7820045, 31T–7820046, 31T–7820047, 31T– 

7820048, 31T–7820049, 31T–7820050, 31T– 

7820051, 31T–7820052, 31T–7820053, 31T– 

7820054, 31T–7820055, 31T–7820056, 31T– 

7820057, 31T–7820058, 31T–7820059, 31T– 

7820060, 31T–7820061, 31T–7820062, 31T– 

7820063, 31T–7820064, 31T–7820065, 31T– 

7820066, 31T–7820067, 31T–7820068, 31T– 

7820069, 31T–7820070, 31T–7820071, 31T– 

7820072, 31T–7820073, 31T–7820074, 31T– 

7820075, 31T–7820076, 31T–7820077, 31T– 

7820078, 31T–7820079, 31T–7820080, 31T– 

7820081, 31T–7820082, 31T–7820083, 31T– 

7820084, 31T–7820085, 31T–7820086, 31T– 

7820087, 31T–7820088, 31T–7820089, 31T– 

7820090, 31T–7820091, 31T–7820092; and 

(2) Model PA–31T1 airplanes, serial 

numbers 31T–7804001, 31T–7804002, 31T– 

7804003, 31T–7804004, 31T–7804005, 31T– 

7804006, 31T–7804007, 31T–7804008, 31T– 

7804009, 31T–7804010, 31T–7804011, 31T– 

7904001, 31T–7904002, 31T–7904003, 31T– 

7904004, 31T–7904005, 31T–7904006, 31T– 

7904007, 31T–7904008, 31T–7904009, 31T– 

7904010, 31T–7904011, 31T–7904012, 31T– 

7904013, 31T–7904014, 31T–7904015, 31T– 

7904016, 31T–7904017, 31T–7904018, 31T– 

7904019, 31T–7904020, 31T–7904021, 31T– 

7904022, 31T–7904023, 31T–7904024, 31T– 

7904025, 31T–7904026, 31T–7904027, 31T– 

7904028, 31T–7904029, 31T–7904030, 31T– 

7904031, 31T–7904032, 31T–7904033, 31T– 

7904034, 31T–7904035, 31T–7904036, 31T– 

7904037, 31T–7904038, 31T–7904039, 31T– 

7904040, 31T–7904041, 31T–7904042, 31T– 

7904043, 31T–7904044, 31T–7904045, 31T– 

7904046, 31T–7904047, 31T–7904048, 31T– 

7904049, 31T–7904050, 31T–7904051, 31T– 

7904052, 31T–7904053, 31T–7904056, 31T– 

7904057. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 1100, Placards and Markings. 

(e) Unsafe Condition 

This AD was prompted by reports that 

some owner/operators of the affected 

airplanes modified the aircraft data plate in 

error because of confusion in the serial 

number applicability. We are issuing this AD 

to correct the unsafe condition on these 

products. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspect the Aircraft Data Plate 

Within the next 100 hours after June 29, 

2012 (the effective date of this AD), inspect 

the markings on the aircraft data plate. Do the 

inspection following Part I of Piper Aircraft, 

Inc. Mandatory Service Bulletin No. 1235, 

dated November 3, 2011. 

(1) If the aircraft data plate is correctly 

marked, make a logbook entry showing 

compliance with this AD, and no further 

action is required. 

(2) If the aircraft data plate is incorrectly 

marked, continue with paragraphs (h) and (i) 

of this AD. 

(h) Modify the Aircraft Data Plate 

Before further flight after the inspection 

required in paragraph (g) of this AD, modify 

the aircraft data plate following Part II of 

Piper Aircraft, Inc. Mandatory Service 

Bulletin No. 1235, dated November 3, 2011. 

(i) Detailed Aircraft Records Search 

Before further flight after the modification 

required in paragraph (h) of this AD: 

(1) Do a detailed search of the aircraft 

maintenance records and documents to 

include, but not limited to, ADs, special 

airworthiness information bulletins (SAIBs), 

service bulletins (SBs), and other service 

documents; installed supplemental type 

certificates (STCs) and parts manufacturing 

approval (PMAs); and instructions for 

continued airworthiness (ICAs). Each 

document found must be assessed to ensure 

proper actions have been made to maintain 

airworthiness as affected by the model 

number of the aircraft. Part 135 operators and 

other operators utilizing FAA-approved 

maintenance programs will need to address 

changes to their inspection programs and 

related documents. 

Note 1 to paragraph (i)(1) of this AD: 

Although some of the above documents may 

not be mandatory for compliance, it is still 

necessary to evaluate them to ensure that any 

voluntary compliance does not negatively 

affect the airworthiness of the airplane. 

(2) Identify all discrepant conditions for 

misidentified aircraft and coordinate with the 

geographic Flight Standards District Office 

(FSDO) and the Atlanta Aircraft Certification 

Office (ACO) to determine necessary 

corrective actions. Also, coordinate with the 

geographic FSDO to arrange for revisions to 

the airworthiness certificate, registration, and 

other potential document/certificate 

revisions. The following is a list of example 

discrepant conditions that may be found 

during the records search: 

(i) An AD was complied with that was 

applicable to the incorrect model, but not 

applicable to the corrected model. 

(ii) A required AD for the corrected model 

was not complied with. 

(iii) A maintenance action was performed 

that was recommended, but not mandatory, 

for the incorrect model, but not applicable to 

the corrected model. 

(iv) A PMA part was installed that was 

applicable for the incorrect model, but not for 

the corrected model. 

(v) An STC was installed that was 

applicable for the incorrect model, but not for 

the corrected model. 

(vi) An STC was installed that was 

applicable for both the incorrect and 

corrected model, but all related, applicable 

ADs for the corrected model were not 

complied with. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Atlanta Aircraft 

Certification Office (ACO), has the authority 

to approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, 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. 

(3) AMOCs approved for AD 80–11–06 (45 

FR 35309, May 27, 1980), are approved as 

AMOCs for this AD. 

(k) Related Information 

For more information about this AD, 

contact Gregory ‘‘Keith’’ Noles, Aerospace 

Engineer, FAA, Atlanta ACO, 1701 Columbia 

Avenue, College Park, Georgia 30337; phone: 

(404) 474–5551; fax: (404) 474–5606; email: 

gregory.noles@faa.gov. 

(l) Material Incorporated by Reference 

(1) You must use Piper Aircraft, Inc. 

Mandatory Service Bulletin No. 1235, dated 

November 3, 2011, to do the actions required 

by this AD, unless the AD specifies 

otherwise. The Director of the Federal 

Register approved the incorporation by 

reference (IBR) under 5 U.S.C. 552(a) and 1 

CFR part 51. 

(2) For service information identified in 

this AD, contact Piper Aircraft, Inc., 926 

Piper Drive, Vero Beach, Florida 32960; 

telephone: (772) 567–4361; Internet: 

www.piper.com. 

(3) You may review copies of the service 

information at the FAA, Small Airplane 

Directorate, 901 Locust, Kansas City, 

Missouri 64106. For information on the 

availability of this material at the FAA, call 

(816) 329–4148. 

(4) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 


wreier-aviles on DSK5TPTVN1PROD with RULES
31172 Federal Register / Vol. 77, No. 102 / Friday, May 25, 2012 / Rules and Regulations 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, call 202–741–6030, or go 

to: http://www.archives.gov/federal-register/

cfr/ibr_locations.html. 

Issued in Kansas City, Missouri, on May 

14, 2012. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2012–12092 Filed 5–24–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0084; Directorate 

Identifier 2010–SW–089–AD; Amendment 

39–17050; AD 2012–10–01] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron Canada Limited 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for Bell 

Helicopter Textron Canada Limited 

(BHTC) Model 427 helicopters which 

requires replacing certain tailboom 

attachment hardware and at certain 

intervals thereafter, determining the 

torque of that tailboom attachment 

hardware. This AD was prompted by a 

review of the tailboom attachment 

installation, which revealed that the 

torque value of the bolts specified in the 

BHTC Model 427 Maintenance Manual 

and applied during manufacturing was 

incorrect and exceeded the torque range 

recommended for the bolts. The actions 

are intended to prevent an over-torque 

of the tailboom attachment bolt (bolt), 

bolt failure, loss of the tailboom, and 

subsequent loss of control of the 

helicopter. 

DATES: This AD is effective June 29, 

2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain documents listed in this AD 

as of June 29, 2012. 

ADDRESSES: 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 http://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. 

Examining the AD Docket: You may 

examine the AD docket on the Internet 

at http://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, any 

incorporated-by-reference service 

information, the economic evaluation, 

any comments received, and other 

information. The street address for the 

Docket Operations Office (phone: 800– 

647–5527) is U.S. Department of 

Transportation, Docket Operations 

Office, M–30, West Building Ground 

Floor, Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Sharon Miles, Aviation Safety Engineer, 

Regulations and Policy Group, 

Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

sharon.y.miles@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On February 3, 2012, at 77 FR 5425, 

the Federal Register published our 

Notice of Proposed Rulemaking 

(NPRM), which proposed to amend 14 

CFR part 39 to include an AD that 

would apply to BHTC Model 427 

helicopters, serial numbers 56001 

through 56084. That NPRM proposed to 

require within 150 hours time-in-service 

(TIS) or 90 days, whichever occurs first, 

the following actions: 

• Remove the left upper bolt, 

washers, and nut. Install the new bolt, 

part number (P/N) NAS627–27; 

washers, P/N 140–007–29S25E6 and P/ 

N NAS1149G0732P; and new nut, P/N 

42FLW–720. Run the nut onto the 

threads of the mating bolt with a torque 

wrench and measure the existing tare 

torque. Any bolt and nut used must 

have a minimum tare torque value of 14 

inch/lbs. Torque the nut and coat the 

bolt head, nut, and washers with 

appropriate corrosion preventive 

compound to seal the joint. Repeat these 

actions at the three remaining bolt 

locations. 

• After installation of the new 

attachment hardware, at intervals of not 

less than 1 hour TIS but not exceeding 

5 hours TIS, determine the torque of 

each nut until torque stabilizes at each 

attachment location. Thereafter, 

determine the torque of each nut at 

intervals not to exceed 300 hours TIS. 

The proposed requirements were 

intended to prevent an over-torque of 

the bolt, bolt failure, loss of the 

tailboom, and subsequent loss of control 

of the helicopter. 

Transport Canada (TC), which is the 

aviation authority for Canada, issued 

Canadian AD CF–2010–32, dated 

September 30, 2010 (AD CF–2010–32), 

to correct an unsafe condition for the 

BHTC Model 427 helicopters, serial 

numbers (S/Ns) 56001 through 56084, 

and S/Ns 58001 and 58002. TC advises 

that a review of the tailboom attachment 

installation determined that the torque 

value of the bolts specified in the BHTC 

Model 427 Maintenance Manual and 

applied during manufacturing exceeded 

the torque range recommended for the 

bolts. They state that this situation, if 

not corrected, could lead to a bolt 

failure, detachment of the tailboom, and 

loss of control of the helicopter. 

Comments 

We gave the public the opportunity to 

participate in developing this AD, but 

we did not receive any comments on the 

NPRM. 

FAA’s Determination 

This helicopter model has been 

approved by the aviation authority of 

Canada and is approved for operation in 

the United States. Pursuant to our 

bilateral agreement with Canada, TC, its 

technical representative, has notified us 

of the unsafe condition described in the 

TC AD. We are issuing this AD because 

we evaluated all information provided 

by TC and determined the unsafe 

condition exists and is likely to exist or 

develop on other helicopters of this 

same type design and that air safety and 

the public interest require adopting the 

AD requirements as proposed. 

Differences Between This AD and the 

TC AD 

The differences between this AD and 

the TC AD are as follows: 

• The TC AD applies to the BHTC 

Model 427 helicopter, serial numbers 

58001 and 58002; however, this AD is 

not applicable to the BHTC Model 427 

helicopters with these serial numbers 

because they are not eligible for an FAA 

Certificate of Airworthiness. 

Related Service Information 

BHTC has issued Alert Service 

Bulletin No. 427–10–31, dated March 1, 

2010 (ASB), which specifies installing 

new attachment hardware with a 

reduced torque value. This ASB 

specifies determining the torque of the 

newly installed bolts and nuts every 1 

to 5 flight hours until torque stabilizes 

at all locations, and thereafter at 

intervals not to exceed 300 flight hours. 

TC classified this ASB as mandatory 

and issued AD CF–2010–32 to ensure 


wreier-aviles on DSK5TPTVN1PROD with RULES