Federal Register / Vol. 75, No. 194 / Thursday, October 7, 2010 / Proposed Rules 61999 

PART 930—PROGRAMS FOR 

SPECIFIC POSITIONS AND 

EXAMINATIONS (MISCELLANEOUS) 

Subpart B—Administrative Law Judge 

Program 

1. The authority citation for subpart B 

continues to read as follows: 

Authority: 5 U.S.C. 1104(a), 1302(a), 1305, 

3105, 3301, 3304, 3323(b), 3344, 4301(2)(D), 

5372, 7521, and E.O. 10577, 3 CFR, 1954– 

1958 Comp., p. 219. 

2. Amend § 930.204 by revising 

paragraph (b) to read as follows: 

§ 930.204 Appointments and conditions of 

employment. 

* * * * * 

(b) Licensure. At the time of 

application and any new appointment, 

the individual must possess a 

professional license to practice law and 

be authorized to practice law under the 

laws of a State, the District of Columbia, 

the Commonwealth of Puerto Rico, or 

any territorial court established under 

the United States Constitution. Judicial 

status is acceptable in lieu of ‘‘active’’ 

status in States that prohibit sitting 

judges from maintaining ‘‘active’’ status 

to practice law. Being in ‘‘good standing’’ 

is also acceptable in lieu of ‘‘active’’ 

status in States where the licensing 

authority considers ‘‘good standing’’ as 

having a current license to practice law. 

* * * * * 

[FR Doc. 2010–25316 Filed 10–6–10; 8:45 am] 

BILLING CODE 6325–39–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0957; Directorate 

Identifier 2010–NM–062–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 767 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede an existing airworthiness 

directive (AD) that applies to certain 

Model 767 airplanes. The existing AD 

currently requires, for certain airplanes, 

reworking the bonding jumper 

assemblies on the drain tube assemblies 

of the slat track housing of the wings. 

For certain other airplanes, the existing 

AD requires repetitive inspections of the 

drain tube assemblies of the slat track 

housing of the wings to find 

discrepancies, corrective actions if 

necessary, and terminating action for 

the repetitive inspections. This 

proposed AD would also require 

replacing the drain tube assemblies. For 

certain airplanes, this proposed AD 

would also require installing an 

additional electrostatic bond path for 

the number 5 and 8 inboard slat track 

drain tube assemblies. For certain other 

airplanes, this proposed AD would also 

require reworking the bonding jumper 

assembly. This proposed AD would also 

revise the applicability to include 

additional airplanes. This proposed AD 

results from reports of fuel leaks from 

certain drain locations of the slat track 

housing near the engine exhaust nozzles 

of the wings, which could result in a fire 

when the airplane is stationary, or 

taxiing at low speed; reports of a 

bonding jumper assembly of certain 

drain tubes that did not meet bonding 

specifications and could result in 

electrostatic discharge and an in-tank 

ignition source; and reports of fuel leaks 

onto the main landing gear (MLG) as a 

result of a cracked drain tube at the 

number 5 or 8 slat track housing, which 

could let fuel drain from the main fuel 

tanks into the dry bay area of the wings 

and onto hot MLG brakes and result in 

a fire. 

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. 

For service information identified in 

this proposed 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; e-mail 

me.boecom@boeing.com; Internet 

https://www.myboeingfleet.com. You 

may review copies of the referenced 

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. 

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: 

Douglas Bryant, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, 

Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

425–227–2384; fax 425–917–6590. 

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–2010–0957; Directorate Identifier 

2010–NM–062–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://

www.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 July 12, 2001, we issued AD 2001– 

14–19, amendment 39–12330 (66 FR 

38350, July 24, 2001), for certain Boeing 

Model 767 airplanes. That AD requires, 

for certain airplanes, reworking the 

bonding jumper assemblies on the drain 

tube assemblies of the slat track housing 

of the wings. For certain other airplanes, 

that AD requires repetitive inspections 

of the drain tube assemblies of the slat 

track housing of the wings to find 

discrepancies, corrective actions if 

necessary, and terminating action for 

the repetitive inspections. That AD was 


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prompted by reports of fuel leaks from 

certain drain locations of the slat track 

housing near the engine exhaust nozzles 

of the wings, which could result in a fire 

when the airplane is stationary or 

during low speed taxiing. That AD was 

also prompted by the discovery that the 

bonding jumper assembly of certain 

drain tube assemblies installed during 

production did not meet the current 

bonding specifications and could result 

in electrostatic discharge and an in-tank 

ignition source. 

Actions Since Existing AD Was Issued 

Since we issued AD 2001–14–19, we 

have received reports of fuel leaks onto 

the MLG of several airplanes due to a 

cracked drain tube at the number 8 slat 

track housing. No fires have been 

reported. The cracking was found on a 

rerouted drain tube with a flexible part. 

(Installing this drain tube is described in 

Boeing Service Bulletin 767–57A0060, 

and is required by AD 2001–14–19.) An 

investigation by Boeing revealed that 

the drain tubes with flexible parts 

cracked as a result of a high intensity 

engine vibration—higher than the tube’s 

design permitted. In one case, 

maintenance personnel observed fuel 

leakage from the pylon area after the 

airplane had landed. 

Relevant Service Information 

AD 2001–14–19 refers to Boeing 

Service Bulletin 767–57A0060, Revision 

1, dated December 31, 1998 (for Model 

767–200, –300, and –300F series 

airplanes), as the appropriate source of 

service information for the repetitive 

inspections and terminating action. 

Boeing has issued Service Bulletin 767– 

57A0060, Revision 2, dated January 31, 

2002, to include minor procedural 

changes. No additional work is 

necessary if the actions specified in 

Boeing Service Bulletin 767–57A0060, 

dated January 30, 1997; or Revision 1, 

dated December 31, 1998; were done. 

AD 2001–14–19 refers to Boeing 

Service Bulletin 767–57–0068, dated 

September 16, 1999 (for Model 767–300 

and –300F series airplanes), as the 

appropriate source of service 

information for reworking the bonding 

jumper assemblies. Boeing has issued 

Boeing Service Bulletin 767–57–0068, 

Revision 1, dated May 9, 2002, which 

corrects an error involving the original 

bonding jumper ‘‘A’’ installation 

sequence. Because of this error, this 

service bulletin specifies that additional 

work, including new rework 

procedures, is necessary. 

We also have reviewed Boeing Service 

Bulletins 767–57A0094 (for Model 767– 

200, –300, and –300F series airplanes) 

and 767–57A0095 (for Model 767– 

400ER series airplanes), both Revision 2, 

both dated December 17, 2009. These 

service bulletins describe procedures for 

replacing drain tube assemblies that 

have flexible parts; the replacement 

assemblies have new aluminum drain 

tubes without flexible parts. 

Boeing Service Bulletin 767– 

57A0094, Revision 2, dated December 

17, 2009, specifies the prior or 

concurrent accomplishment, for certain 

airplanes, of Boeing Service Bulletins 

767–57A0060, Revision 2, dated January 

31, 2002; and 767–57–0068, Revision 1, 

dated May 9, 2002. 

FAA’s Determination and Requirements 

of the Proposed AD 

We have evaluated all pertinent 

information and identified an unsafe 

condition that is likely to develop on 

other airplanes of the same type design. 

For this reason, we are proposing this 

AD, which would supersede AD 2001– 

14–19 and retain the requirements of 

that AD. This proposed AD would also 

require accomplishing the new actions 

specified in the service information 

described previously, except as 

described below. 

Difference Between Service Bulletin 

and Proposed AD 

Boeing Service Bulletin 767–57–0068, 

Revision 1, dated May 9, 2002, specifies 

that the compliance time to rework the 

bonding jumper assembly (required by 

paragraph (l) of this NPRM) is 48 

months after that date. In developing an 

appropriate compliance time for this 

action, we considered the safety 

implications, parts availability, and 

normal maintenance schedules for the 

timely accomplishment of the 

modification. We also considered that 

this work, if not previously 

accomplished as an AMOC to AD 2001– 

14–19, must be done concurrently with 

the new requirements of this proposed 

AD. 

Changes to Existing AD 

This proposed AD would revise the 

applicability of AD 2001–14–19 by 

adding line numbers 758 through 921, 

which were produced since that AD was 

issued. Those airplanes had received a 

production change equivalent to the 

actions required by the existing AD, and 

are now subject to the identified unsafe 

condition. 

This proposed AD would retain the 

requirements of AD 2001–14–19. Since 

that AD was issued, the AD format has 

been revised, and certain paragraphs 

have been rearranged. As a result, the 

corresponding paragraph identifiers 

have changed in this proposed AD, as 

listed in the following table: 

REVISED PARAGRAPH IDENTIFIERS

Requirement in AD 

2001–14–19 

Corresponding 

requirement in 

this proposed AD 

paragraph (a) paragraph (g) 

paragraph (b) paragraph (h) 

paragraph (c) paragraph (i) 

Costs of Compliance 

There are about 808 airplanes of the 

affected design in the worldwide fleet. 

The following table provides the 

estimated costs for U.S. operators to 

comply with this proposed AD. The 

average labor rate is $85 per hour. 

ESTIMATED COSTS

Action Work hours Parts Cost per airplane 

Number of 

U.S.- 

registered 

airplanes 

Fleet cost 

Inspection (required by AD 2001–14–19) ... 1 ............................... $0 $85 per inspection 

cycle.

255 $21,675 per inspection cycle. 

Drain tube replacement (required by AD 

2001–14–19).

12 ............................. 5,236 $6,256 ...................... 255 $1,595,280. 

Bonding jumper assembly rework (required 

by AD 2001–14–19).

4 ............................... 322 $662 ......................... 47 $31,114. 

Drain tube replacement (new proposed action).Between 7 and 11, 

depending on configuration.

1,117 Between $1,712 and 

$2,052.

356 Between $609,472 

and $730,512. 


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Federal Register / Vol. 75, No. 194 / Thursday, October 7, 2010 / Proposed Rules 62001 

ESTIMATED COSTS—Continued 

Action Work hours Parts Cost per airplane 

Number of 

U.S.- 

registered 

airplanes 

Fleet cost 

Installation of electrostatic bond path (new 

proposed action).

4 ............................... 322 $662 ......................... 47 $31,114. 

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 

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 that the 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. See the ADDRESSES section 

for a location to examine the regulatory 

evaluation. 

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 39–12330 (66 FR 

38350, July 24, 2001) and adding the 

following new AD: 

The Boeing Company: Docket No. FAA– 

2010–0957; Directorate Identifier 2010– 

NM–062–AD. 

Comments Due Date 

(a) The FAA must receive comments on 

this AD action by November 22, 2010. 

Affected ADs 

(b) This AD supersedes AD 2001–14–19, 

Amendment 39–12330. 

Applicability 

(c) This AD applies to the airplanes, 

certificated in any category, identified in 

paragraphs (c)(1) and (c)(2) of this AD. 

(1) Model 767–200, –300, and –300F series 

airplanes, as identified in Boeing Service 

Bulletin 767–57A0094, Revision 2, dated 

December 17, 2009. 

(2) Model 767–400ER series airplanes, as 

identified in Boeing Service Bulletin 767– 

57A0095, Revision 2, dated December 17, 

2009. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 57: Wings. 

Unsafe Condition 

(e) This AD results from reports of fuel 

leaks from certain drain locations of the slat 

track housing near the engine exhaust 

nozzles of the wings, which could result in 

a fire when the airplane is stationary, or 

taxiing at low speed; reports of a bonding 

jumper assembly of certain drain tubes that 

did not meet bonding specifications and 

could result in electrostatic discharge and an 

in-tank ignition source; and reports of fuel 

leaks onto the main landing gear (MLG) as a 

result of a cracked drain tube at the number 

5 or 8 slat track housing, which could let fuel 

drain from the main fuel tanks into the dry 

bay area of the wings and onto hot MLG 

brakes and result in a fire. 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Restatement of Requirements of AD 2001– 

14–19, AMENDMENT 39–12330, With 

Revised Service Information 

Repetitive Inspections/Corrective Action 

(g) For airplanes identified in Boeing 

Service Bulletin 767–57A0060, Revision 1, 

dated December 31, 1998: Within 500 flight 

hours after August 28, 2001 (the effective 

date of AD 2001–14–19), do a general visual 

inspection of the drain tube assemblies of the 

slat track housings of the wings to find 

discrepancies (loose fittings, cracked tubes, 

fuel leaks), per Part I 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. 

(1) If any discrepancies are found, before 

further flight, rework the drain tube assembly 

per Part II 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. Repeat the 

inspection at intervals not to exceed 500 

flight hours until accomplishment of the 

requirements in paragraph (h) of this AD. 

(2) If no discrepancies are found, repeat the 

inspection thereafter at intervals not to 

exceed 500 flight hours, until 

accomplishment of the requirements in 

paragraph (h) of this AD. 

Note 1: For the purposes of this AD, a 

general visual inspection is defined as: ‘‘A 

visual examination of an interior or exterior 

area, installation, or assembly to find obvious 

damage, failure, or irregularity. This level of 

inspection is made under normally available 

lighting conditions such as daylight, hangar 

lighting, flashlight, or drop-light and may 

require removal or opening of access panels 

or doors. Stands, ladders, or platforms may 

be required to gain proximity to the area 

being checked.’’ 

Terminating Action for Repetitive 

Inspections 

(h) For airplanes specified in paragraph (g) 

of this AD: Within 6,000 flight hours or 24 


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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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