62002 Federal Register / Vol. 75, No. 194 / Thursday, October 7, 2010 / Proposed Rules 

months after August 28, 2001, whichever 

occurs first, replace the drain tube assemblies 

of the slat track housings of the wings 

(including general visual inspection and 

repair) per Part III of the Accomplishment 

Instructions of Boeing Service Bulletin 767– 

57A0060, Revision 1, dated December 31, 

1998; or Revision 2, dated January 31, 2002. 

After the effective date of this AD, only 

Revision 2 may be used. Any applicable 

repair must be accomplished prior to further 

flight. Accomplishment of this paragraph 

terminates the repetitive inspections required 

by paragraph (g) of this AD. 

Rework of Bonding Jumper Assemblies 

(i) For airplanes identified in Boeing 

Service Bulletin 767–57–0068, dated 

September 16, 1999: Within 5,000 flight 

cycles or 22 months after August 28, 2001, 

whichever occurs first, rework the bonding 

jumper assembly of the drain tube assemblies 

of the slat track housing of the wings 

(including general visual inspection and 

repair) per the Accomplishment Instructions 

of Boeing Service Bulletin 767–57–0068, 

dated September 16, 1999; or Revision 1, 

dated May 9, 2002. After the effective date of 

this AD, only Revision 1 may be used. Any 

applicable repair must be accomplished prior 

to further flight. 

New Requirements of this AD 

Drain Tube Replacement 

(j) Within 24 months after the effective date 

of this AD, replace affected drain tube 

assemblies of the number 5 and number 8 

inboard slat track housing, in accordance 

with the Accomplishment Instructions of 

Boeing Service Bulletin 767–57A0094 (for 

Model 767–200, –300, and –300F series 

airplanes) or 767–57A0095 (for Model 767– 

400ER series airplanes), both Revision 2, both 

dated December 17, 2009. 

Concurrent Requirements 

(k) For airplanes in Groups 1, 2, and 3, as 

identified in Boeing Service Bulletin 767– 

57A0094, Revision 2, dated December 17, 

2009: The actions specified in paragraphs 

(k)(1), (k)(2), and (k)(3) of this AD, as 

applicable, must be done before or 

concurrently with the requirements of 

paragraph (j) of this AD. 

(1) For Groups 1 and 2: The requirements 

of paragraph (h) of this AD. 

(2) For Group 2 airplanes: Installation of an 

additional electrostatic bond path for the 

number 5 and 8 inboard slat track drain tube 

assemblies, in accordance with Part IV of the 

Accomplishment Instructions of Boeing 

Service Bulletin 767–57A0060, Revision 1, 

dated December 31, 1998; or Revision 2, 

dated January 31, 2002. 

(3) For Group 3 airplanes: The 

requirements of paragraph (i) of this AD. 

(l) For airplanes identified in paragraph (i) 

of this AD, on which the actions required by 

paragraph (i) of this AD were done before the 

effective date of this AD in accordance with 

Boeing Service Bulletin 767–57–0068, dated 

September 16, 1999: Prior to or concurrently 

with the requirements of paragraph (j) of this 

AD, rework the bonding jumper assembly for 

the number 5 and 8 inboard slat track 

housing drain tube installation, in 

accordance with Part 2 of the 

Accomplishment Instructions of Boeing 

Service Bulletin 767–57–0068, Revision 1, 

dated May 9, 2002. 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(m) Actions done before the effective date 

of this AD in accordance with an applicable 

service bulletin identified in Table 1 of this 

AD are acceptable for compliance with the 

corresponding requirements of paragraph (j) 

of this AD. 

TABLE 1—CREDIT SERVICE BULLETINS

Affected airplanes Service Bulletin Revision level Date 

Model 767–200, –300, and –300F series airplanes.Boeing Service Bulletin 767–57A0094 ........... Original .......................

1 .................................

June 2, 2005. 

December 19, 2006. 

Model 767–400ER series airplanes ................. Boeing Service Bulletin 767–57A0095 ........... Original .......................

1 .................................

June 2, 2005. 

December 19, 2006. 

Alternative Methods of Compliance 

(AMOCs) 

(n)(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. Send information to ATTN: 

Douglas Bryant, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, Seattle 

ACO, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 425– 

227–2384; fax 425–917–6590. Information 

may be e-mailed to 9-ANM-Seattle-ACOAMOC-Requests@faa.gov. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards District 

Office. The AMOC approval letter must 

specifically refer to this AD. 

(3) AMOCs approved previously in 

accordance with AD 2001–14–19, 

Amendment 39–12330, are approved as 

AMOCs for the corresponding provisions of 

this AD. 

Issued in Renton, Washington, on October 

1, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–25255 Filed 10–6–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1011; Directorate 

Identifier 2010–CE–047–AD] 

RIN 2120–AA64 

Airworthiness Directives; Pilatus 

Aircraft Ltd. Models PC–6, PC–6–H1, 

PC–6–H2, PC–6/350, PC–6/350–H1, PC– 

6/350–H2, PC–6/A, PC–6/A–H1, PC–6/ 

A–H2, PC–6/B–H2, PC–6/B1–H2, PC–6/ 

B2–H2, PC–6/B2–H4, PC–6/C–H2, and 

PC–6/C1–H2 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above that would 

supersede an existing AD. This 

proposed AD results from mandatory 

continuing airworthiness information 

(MCAI) originated by an aviation 

authority of another country to identify 

and correct an unsafe condition on an 

aviation product. The MCAI describes 

the unsafe condition as: 

The current Aircraft Maintenance Manual 

(AMM) of PC–6 B2–H2 and B2–H4 models 

does not include a Chapter 04 in the 

Airworthiness Limitations Section (ALS). For 

PC–6 models other than B2–H2 and B2–H4, 

no ALS at all is included in the AMM. 

With the latest Revision 12 of the AMM, 

a new Chapter 04 has been introduced in the 

AMM for PC–6 B2–H2 and B2–H4 models. 

For PC–6 models other than B2–H2 and 

B2–H4, a new ALS document has been 

implemented as well. 

These documents include the Mandatory 

Continuing Airworthiness Information 

(MCAI) which are maintenance requirements 

and/or airworthiness limitations developed 

by Pilatus Aircraft Ltd and approved by 


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Federal Register / Vol. 75, No. 194 / Thursday, October 7, 2010 / Proposed Rules 62003 

EASA. Failure to comply with these MCAI 

constitutes an unsafe condition. 

The proposed AD would require actions 

that are intended to address the unsafe 

condition described in the MCAI. 

DATES: We must receive comments on 

this proposed AD by November 22, 

2010. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590, 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 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 proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(telephone (800) 647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Doug Rudolph, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 

Locust, Room 301, Kansas City, 

Missouri 64106; telephone: (816) 329– 

4059; fax: (816) 329–4090. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2010–1011; Directorate Identifier 

2010–CE–047–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD because of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

regulations.gov, including any personal 

information you provide. We will also 

post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

On August 8, 2005, we issued AD 

2005–17–01, Amendment 39–14221 (70 

FR 47716; August 15, 2005). This AD 

required actions intended to address an 

unsafe condition on the products listed 

above. 

Since we issued AD 2005–17–01, 

Pilatus has updated their maintenance 

programs with new requirements and 

limitations. The AMM revisions 

proposed in this AD action include the 

repetitive inspections for the wing strut 

fittings and the spherical bearings 

currently included in AD 2009–18–03. 

We are also proposing to remove those 

repetitive inspections from AD 2009– 

18–03. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA AD No.: 

2010–0176, dated August 20, 2010 

(referred to after this as ‘‘the MCAI’’), to 

correct an unsafe condition for the 

specified products. The MCAI states: 

The current Aircraft Maintenance Manual 

(AMM) of PC–6 B2–H2 and B2–H4 models 

does not include a Chapter 04 in the 

Airworthiness Limitations Section (ALS). For 

PC–6 models other than B2–H2 and B2–H4, 

no ALS at all is included in the AMM. 

With the latest Revision 12 of the AMM, 

a new Chapter 04 has been introduced in the 

AMM for PC–6 B2–H2 and B2–H4 models. 

For PC–6 models other than B2–H2 and 

B2–H4, a new ALS document has been 

implemented as well. 

These documents include the Mandatory 

Continuing Airworthiness Information 

(MCAI) which are maintenance requirements 

and/or airworthiness limitations developed 

by Pilatus Aircraft Ltd and approved by 

EASA. Failure to comply with these MCAI 

constitutes an unsafe condition. 

For the reasons described above, this AD 

requires the implementation and the 

compliance with these new maintenance 

requirements and/or airworthiness 

limitations documents. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Pilatus Aircraft Limited has issued 

Pilatus PC–6 Aircraft Maintenance 

Manual (AMM) Chapter 04–00–00, 

Revision 12, Document 01975, dated 

May 14, 2010, for Models PC–6 B2–H2 

and B2–H4 airplanes, and Pilatus PC–6 

Airworthiness Limitations Section 

(ALS) document No. 02334, revision 1, 

dated May 14, 2010, for all other Model 

PC–6 airplanes. The actions described 

in this service information are intended 

to correct the unsafe condition 

identified in the MCAI. 

FAA’s Determination and Requirements 

of the Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with this State of 

Design Authority, they have notified us 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Differences Between This Proposed AD 

and the MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have proposed 

different actions in this AD from those 

in the MCAI in order to follow FAA 

policies. Any such differences are 

highlighted in a Note within the 

proposed AD. 

Costs of Compliance 

We estimate that this proposed AD 

will affect 50 products of U.S. registry. 

We also estimate that it would take 

about 1 work-hour per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. 

Based on these figures, we estimate 

the cost of the proposed AD on U.S. 

operators to be $4,250, or $85 per 

product. 

In addition, we estimate that any 

necessary follow-on actions based on 

maintenance requirements for the wing 

strut fittings and the spherical bearings 

following the Aircraft Maintenance 

Manual and the Airworthiness 

Limitations Section would take about 40 

work-hours and require parts costing 

$12,000, for a cost of $15,400 per 

product. We have no way of 

determining the number of products 

that may need these actions. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 


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62004 Federal Register / Vol. 75, No. 194 / Thursday, October 7, 2010 / Proposed Rules 

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 proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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 this proposed regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this proposed 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. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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 39–14221 (70 FR 

47716; August 15, 2005), and adding the 

following new AD: 

Pilatus Aircraft Ltd.: Docket No. FAA–2010– 

1011; Directorate Identifier 2010–CE– 

047–AD. 

Comments Due Date 

(a) We must receive comments by 

November 22, 2010. 

Affected ADs 

(b) This AD supersedes AD 2005–17–01, 

Amendment 39–14221. 

Applicability 

(c) This AD applies to Pilatus Aircraft Ltd. 

Models PC–6, PC–6–H1, PC–6–H2, PC–6/350, 

PC–6/350–H1, PC–6/350–H2, PC–6/A, PC–6/ 

A–H1, PC–6/A–H2, PC–6/B–H2, PC–6/B1– 

H2, PC–6/B2–H2, PC–6/B2–H4, PC–6/C–H2, 

and PC–6/C1–H2 airplanes, all manufacturer 

serial number (MSN), and MSN 2001 through 

2092, certificated in any category. These 

airplanes are also identified as Fairchild 

Republic Company PC–6 airplanes, Fairchild 

Industries PC–6 airplanes, Fairchild Heli 

Porter PC–6 airplanes, or Fairchild-Hiller 

Corporation PC–6 airplanes. 

Subject 

(d) Air Transport Association of America 

(ATA) Code 5: Time Limits. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

The current Aircraft Maintenance Manual 

(AMM) of PC–6 B2–H2 and B2–H4 models 

does not include a Chapter 04 in the 

Airworthiness Limitations Section (ALS). For 

PC–6 models other than B2–H2 and B2–H4, 

no ALS at all is included in the AMM. 

With the latest Revision 12 of the AMM, 

a new Chapter 04 has been introduced in the 

AMM for PC–6 B2–H2 and B2–H4 models. 

For PC–6 models other than B2–H2 and 

B2–H4, a new ALS document has been 

implemented as well. 

These documents include the Mandatory 

Continuing Airworthiness Information 

(MCAI) which are maintenance requirements 

and/or airworthiness limitations developed 

by Pilatus Aircraft Ltd and approved by 

EASA. Failure to comply with these MCAI 

constitutes an unsafe condition. 

For the reasons described above, this MCAI 

requires the implementation and the 

compliance with these new maintenance 

requirements and/or airworthiness 

limitations documents. 

Actions and Compliance 

(f) Unless already done, before further 

flight after the effective date of this AD, 

incorporate the maintenance requirements as 

specified in Pilatus PC–6 AMM Chapter 04– 

00–00, Revision 12, Document Number 

01975, dated May 14, 2010; and incorporate 

the Pilatus PC–6 ALS Document Number 

02334, Revision 1, dated May 14, 2010, into 

your FAA-accepted maintenance program. 

Note 1: The AMM revisions proposed in 

this AD action include the repetitive 

inspections for the wing strut fittings and the 

spherical bearings currently included in AD 

2009–18–03. We are also proposing to 

remove those repetitive inspections from AD 

2009–18–03, through a revision in another 

NPRM, Docket No. FAA–2009–0622. 

FAA AD Differences 

Note 2: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(g) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Office, 

FAA, has the authority to approve AMOCs 

for this AD, if requested using the procedures 

found in 14 CFR 39.19. Send information to 

ATTN: Doug Rudolph, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4059; fax: (816) 329– 

4090. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your appropriate principal inspector 

(PI) in the FAA Flight Standards District 

Office (FSDO), or lacking a PI, your local 

FSDO. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act 

(44 U.S.C. 3501 et. seq.), the Office of 

Management and Budget (OMB) has 

approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(h) Refer to MCAI EASA AD No.: 2010– 

0176, dated August 20, 2010; and Pilatus PC– 

6 AMM Chapter 04–00–00, Revision 12, 

Document Number 01975, Revision 12, dated 

May 14, 2010; or in the Pilatus PC–6 ALS 

Document Number 02334, Revision 1, dated 

May 14, 2010, for related information. 

Issued in Kansas City, Missouri, on 

September 30, 2010. 

John Colomy, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–25288 Filed 10–6–10; 8:45 am] 

BILLING CODE 4910–13–P 


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