Federal Register / Vol. 62, No. 195 / Wednesday, October 8, 1997 / Rules and Regulations 52489

than 80 pounds per square inch, gauge (psig);

or

(2) Incorporate the following Temporary

Revision(s) to Chapter 12 of the Boeing

Model 737 Airplane Maintenance Manual

(AMM), all dated February 7, 1997; as

applicable; into the FAA-approved

maintenance program.

Airplane model

Temporary

revision

No.

737–100/200 ................................... 12–368

12–369

12–370

12–371

12–372

12–373

737–300/–400/–500 ........................ 12–85

Note 2: Once an operator has incorporated

the above procedures into its maintenance

program, this AD does not require that the

operator subsequently record

accomplishment each time the wheel well is

cleaned. Future changes to the above

maintenance program require prior approval

of an appropriate FAA Principal

Maintenance Inspector (PMI).

(b) An alternative method of compliance or

adjustment of the compliance time that

provides an acceptable level of safety may be

used if approved by the Manager, Seattle

Aircraft Certification Office (ACO), FAA,

Transport Airplane Directorate. Operators

shall submit their requests through an

appropriate FAA PMI, who may add

comments and then send it to the Manager,

Seattle ACO.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Seattle ACO.

(c) Special flight permits may be issued in

accordance with sections 21.197 and 21.199

of the Federal Aviation Regulations (14 CFR

21.197 and 21.199) to operate the airplane to

a location where the requirements of this AD

can be accomplished.

(d) Except as specified in paragraph (a)(1)

of this AD, the actions shall be done in

accordance with the following Temporary

Revisions to Chapter 12 of the Boeing Model

737 Airplane Maintenance Manual.

Airplane model

Temporary

revision

No.

Dated

737–100/200 ...... 12–368 Feb. 7, 1997.

12–369 Feb. 7, 1997.

12–370 Feb. 7, 1997.

12–371 Feb. 7, 1997.

12–372 Feb. 7, 1997.

12–373 Feb. 7, 1997.

737–300/–400/–

500.

12–85 Feb. 7, 1997.

The incorporation by reference was approved

by the Director of the Federal Register in

accordance with 5 U.S.C. 552(a) and 1 CFR

part 51. Copies may be obtained from Boeing

Commercial Airplane Group, P.O. Box 3707,

Seattle, Washington 98124–2207. Copies may

be inspected at the FAA, Transport Airplane

Directorate, 1601 Lind Avenue, SW., Renton,

Washington; or at the Office of the Federal

Register, 800 North Capitol Street, NW., suite

700, Washington.

(e) This amendment becomes effective on

November 12, 1997.

Issued in Renton, Washington, on August

25, 1997.

James V. Devany,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–24334 Filed 10–7–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96–SW–32–AD; Amendment

39–10151; AD 97–20–15]

RIN 2120–AA64

Airworthiness Directives; Hiller Aircraft

Corporation Model UH–12A, UH–12B,

UH–12C, UH–12D, and UH–12E

Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to Hiller Aircraft Corporation

Model UH–12A, UH–12B, UH–12C,

UH–12D, and UH–12E helicopters, that

currently requires a dye penetrant

inspection of the head of the main rotor

outboard tension-torsion (T–T) bar pin

for cracks; a visual inspection of the

outboard T–T bar pin for proper

alignment and an adjustment, if

necessary; and, installation of shims at

the inboard end of the drag strut. This

amendment requires the same actions

required by the existing AD, but allows

a magnetic particle inspection of the T–

T bar pin as an alternative to the

currently required dye penetrant

inspection, and requires reporting the

results of the inspections only if cracks

are found, rather than reporting all

results of inspections as required by the

existing AD. This amendment is

prompted by an FAA analysis of a

comment to the existing AD, and the

fact that no cracks have been reported

since the issuance of the existing AD.

The actions specified by this AD are

intended to prevent cracks in the head

area of the outboard T–T bar pin, which

could result in loss of in-plane stability

of the main rotor blade and subsequent

loss of control of the helicopter.

DATES: Effective November 12, 1997.

The incorporations by reference of

certain publications listed in the

regulations were approved by the

Director of the Federal Register as of

June 23, 1995 (60 FR 30184, June 8,

1995).

ADDRESSES: The service information

referenced in this AD may be obtained

from Hiller Aircraft Corporation, 3200

Imjin Road, Marina, California 93933–

5101, telephone (408) 384–4500, fax

(408) 883–3648. This information may

be examined at the FAA, Office of the

Assistant Chief Counsel, 2601 Meacham

Blvd., Room 663, Fort Worth, Texas; or

at the Office of the Federal Register, 800

North Capitol Street, NW., suite 700,

Washington, DC.

FOR FURTHER INFORMATION CONTACT: Mr.

Charles Matheis, Aerospace Engineer,

FAA, Los Angeles Aircraft Certification

Office, 3960 Paramount Blvd.,

Lakewood, California 90712–4137,

telephone (562) 627–5235, fax (562)

627–5210.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39)

by superseding AD 95–12–02,

Amendment 39–9252 (60 FR 30184),

which is applicable to Hiller Model

UH–12A, UH–12B, UH–12C, UH–12D,

and UH–12E helicopters, was published

in the Federal Register on January 7,

1997 (62 FR 951). That action proposed

to require (1) an inspection of the

alignment of the outboard T–T bar pin

and an adjustment, if necessary; and (2)

an inspection for cracks in the head of

the outboard T–T bar pin using a dye

penetrant method or a magnetic particle

method. Additionally, that action

proposed to require, within 25 hours

TIS or at the next 100 hour inspection,

whichever occurs first, the installation

of shims between the inboard end of the

drag strut and the outboard T–T bar pin.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comment received.

The one commenter states that AD

95–12–02 should be eliminated, and

that the requirement to report results of

each 100 hour TIS inspection to the

FAA should be discontinued, unless a

crack is found. The commenter states

that they have not experienced a T–T

bar pin failure in 30 years of service

history, and that if the procedures in the

manufacturer’s service information is

followed, the AD is not needed. The

FAA concurs that the reporting of the

inspection should be accomplished only

if the inspection reveals a crack.

However, the FAA does not concur that

the AD should be eliminated. The
52490 Federal Register / Vol. 62, No. 195 / Wednesday, October 8, 1997 / Rules and Regulations

National Transportation Safety Board

recommended that the FAA issue an AD

to make the requirements of the

applicable service information

mandatory. The FAA concurred, and

issued AD 95–12–02. Based on an FAA

analysis, the FAA has determined that

the amendment will not be removed,

but the reporting requirement will be

changed.

After careful review of the available

data, including the comments noted

above, the FAA has determined that air

safety and the public interest require the

adoption of the rule as proposed.

The FAA estimates that 700

helicopters of U.S. registry will be

affected by this AD, that it will take

approximately 2 work hours per

helicopter to accomplish the required

actions, and that the average labor rate

is $60 per work hour. Required parts

will cost approximately $700 per pin.

Based on these figures, the total cost

impact of the AD on U.S. operators is

estimated to be $574,000, assuming one

pin must be replaced on every

helicopter in the fleet.

The regulations adopted herein will

not have substantial direct effects on the

States, on the relationship between the

national government and the States, or

on the distribution of power and

responsibilities among the various

levels of government. Therefore, in

accordance with Executive Order 12612,

it is determined that this final rule does

not have sufficient federalism

implications to warrant the preparation

of a Federalism Assessment.

For the reasons discussed above, I

certify that this action (1) is not a

‘‘significant regulatory action’’ under

Executive Order 12866; (2) is not a

‘‘significant rule’’ under DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979); and (3)

will not have a significant economic

impact, positive or negative, on a

substantial number of small entities

under the criteria of the Regulatory

Flexibility Act. A final evaluation has

been prepared for this action and it is

contained in the Rules Docket. A copy

of it may be obtained from the Rules

Docket at the location provided under

the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Incorporation by reference,

Safety.

Adoption of the Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration amends part 39 of the

Federal Aviation Regulations (14 CFR

part 39) as follows:

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. Section 39.13 is amended by

removing Amendment 39–9252 (60 FR

30184), and by adding a new

airworthiness directive (AD),

Amendment 39–10151, to read as

follows:

97–20–15 Hiller Aircraft Corporation:

Amendment 39–10151. Docket No. 96–

SW–32–AD. Supersedes AD 95–12–02,

Amendment 39–9252.

Applicability: Model UH–12A, UH–12B,

UH–12C, UH–12D, and UH–12E helicopters,

certificated in any category.

Note 1: This AD applies to each helicopter

identified in the preceding applicability

provision, regardless of whether it has been

modified, altered, or repaired in the area

subject to the requirements of this AD. For

helicopters that have been modified, altered,

or repaired so that the performance of the

requirements of this AD is affected, the

owner/operator must use the authority

provided in paragraph (e) to request approval

from the FAA. This approval may address

either no action, if the current configuration

eliminates the unsafe condition, or different

actions necessary to address the unsafe

condition described in this AD. Such a

request should include an assessment of the

effect of the changed configuration on the

unsafe condition addressed by this AD. In no

case does the presence of any modification,

alteration, or repair remove any helicopter

from the applicability of this AD.

Compliance: Required as indicated, unless

accomplished previously.

To prevent cracks in the head area of the

outboard tension-torsion (T–T) bar pin,

which could result in loss of in-plane

stability of the main rotor blade and

subsequent loss of control of the helicopter,

accomplish the following:

(a) Within 25 hours time-in-service (TIS)

after the effective date of this AD, or at the

next 100 hour inspection, whichever occurs

first, and thereafter at intervals not to exceed

100 hours TIS, inspect the alignment of the

outboard T–T bar pin, part number (P/N)

51452, and adjust the alignment, if necessary,

in accordance with Hiller Aviation Service

Letter (SL) 51–2, dated March 31, 1978.

(b) Within 25 hours TIS after the effective

date of this AD, or at the next 100 hour

inspection, whichever occurs first, and

thereafter at intervals not to exceed 100 hours

TIS, inspect the head of the outboard T–T bar

pin for cracks using a dye penetrant or

magnetic particle inspection method.

(c) If a crack is found as a result of the

inspection required by paragraph (b) of this

AD, report the results within 7 working days

following the inspection to the Manager, Los

Angeles Aircraft Certification Office,

Attention Charles Matheis, ANM–120L, 3960

Paramount Blvd., Lakewood, California

90712–4137. Include the helicopter model

number, serial number, and total TIS of the

outboard T–T bar pin in the report. Reporting

requirements have been approved by the

Office of Management and Budget and

assigned OMB control number 2120–0056.

(d) Within 25 hours TIS after the effective

date of this AD, or at the next 100 hour

inspection, whichever occurs first, install

shims between the inboard end of the drag

strut and the outboard T–T bar pin in

accordance with the Accomplishment

Instructions of Hiller Aviation Service

Bulletin No. 51–9, dated April 8, 1983.

(e) An alternative method of compliance or

adjustment of the compliance time that

provides an acceptable level of safety may be

used if approved by the Manager, Los

Angeles Aircraft Certification Office, FAA.

Operators shall submit their requests through

an FAA Principal Maintenance Inspector,

who may concur or comment and then send

it to the Manager, Los Angeles Aircraft

Certification Office.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Los Angeles Aircraft

Certification Office.

(f) Special flight permits may be issued in

accordance with sections 21.197 and 21.199

of the Federal Aviation Regulations (14 CFR

21.197 and 21.199) to operate the helicopter

to a location where the requirements of this

AD can be accomplished.

(g) The adjustment of the alignment of the

T–T bar pin shall be done in accordance with

Hiller Aviation SL 51–2, dated March 31,

1978, and the installation of the shims shall

be done in accordance with Hiller Aviation

Service Bulletin No. 51–9, dated April 8,

1983. These incorporations by reference were

approved by the Director of the Federal

Register in accordance with 5 U.S.C. 552(a)

and 1 CFR part 51 as of June 23, 1995 (60

FR 30184, June 8, 1995). Copies may be

obtained from Hiller Aircraft Corporation,

3200 Imjin Road, Marina, California 93933–

5101, telephone (408) 384–4500, fax (408)

883–3648. Copies may be inspected at the

FAA, Office of the Assistant Chief Counsel,

2601 Meacham Blvd., Room 663, Fort Worth,

Texas; or at the Office of the Federal Register,

800 North Capitol Street, NW., suite 700,

Washington, DC.

(h) This amendment becomes effective on

November 12, 1997.

Issued in Fort Worth, Texas, on September

26, 1997.

Eric Bries,

Acting Manager, Rotorcraft Directorate,

Aircraft Certification Service.

[FR Doc. 97–26621 Filed 10–7–97; 8:45 am]

BILLING CODE 4910–13–U