Federal Register / Vol. 62, No. 41 / Monday, March 3, 1997 / Rules and Regulations 9359

authorize the use of FO funds for

include, but are not limited to, the

construction, purchase, and

improvement of farm dwellings, service

buildings and facilities that can be made

fixtures to the real estate.

(3) Promote soil and water

conservation and protection. Examples

include the correction of well-defined,

hazardous environmental conditions,

and the construction or installation of

tiles, terraces and waterways.

(4) Pay closing costs, including but

not limited to purchasing stock in a

cooperative, and appraisal and survey

fees.

(5) Refinancing indebtedness incurred

for authorized loan purposes, provided

the lender and loan applicant

demonstrate the need to refinance the

debt.

* * * * *

Signed at Washington, D.C., on February

19, 1997.

Dallas R. Smith,

Acting Under Secretary for Farm and Foreign

Agricultural Services.

Jill Long Thompson,

Under Secretary for Rural Development.

[FR Doc. 97–4840 Filed 2–28–97; 8:45 am]

BILLING CODE 3410–05–M

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–32–AD; Amendment

39–9952; AD 97–05–08]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 727 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that is

applicable to all Boeing Model 727

series airplanes. This action requires

repetitive pre-modification inspections

to detect cracks in the forward support

fitting of the number 1 and number 3

engines; and repair, if necessary. This

AD also provides for an optional high

frequency eddy current (HFEC)

inspection, and, if possible,

modification of the fastener holes; and

various follow-on actions.

Accomplishment of these optional

actions would constitute terminating

action for the repetitive premodification inspections. This

amendment is prompted by reports

indicating that fatigue cracks were

found in the forward support fitting of

the number 1 and number 3 engines.

The actions specified in this AD are

intended to detect and correct such

fatigue cracking, which could result in

failure of the support fitting and

consequent separation of the engine

from the airplane.

DATES: Effective March 18, 1997.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of March 18,

1997.

Comments for inclusion in the Rules

Docket must be received on or before

May 2, 1997.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 97–NM–

32–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

The service information referenced in

this AD may be obtained from Boeing

Commercial Airplane Group, P.O. Box

3707, Seattle, Washington 98124–2207.

This information may be examined 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, DC.

FOR FURTHER INFORMATION CONTACT:

Walter Sippel, Aerospace Engineer,

Airframe Branch, ANM–120S, FAA,

Seattle Aircraft Certification Office,

1601 Lind Avenue, SW., Renton,

Washington; telephone (206) 227–2774;

fax (206) 227–1181.

SUPPLEMENTARY INFORMATION: The FAA

has received several reports of cracks

found in the forward support fitting of

the number 1 and number 3 engines on

Boeing Model 727 series airplanes. In

two of these incidents, the cracks

emanated from the large fastener holes

next to the side of the fuselage. In a

third incident, a fitting was cracked

almost completely through. In other

incidents, cracks were found at a small

distance inboard from the fuselage side.

The cracking has been attributed to

fatigue, which was caused by corrosion

pitting damage on the surfaces of the

fastener holes in the fittings. These

conditions, if not detected and corrected

in a timely manner, could result in

failure of the support fitting and

consequent separation of the engine

from the airplane.

Explanation of Relevant Service

Information

The FAA has reviewed and approved

Boeing Service Bulletin 727–54A0010,

Revision 4, dated January 30, 1997,

which describes the following

procedures:

1. Performing repetitive visual

inspections to detect cracks of the upper

and lower flanges, and the vertical web

of the forward support fitting of the

number 1 and number 3 engines;

2. Performing repetitive high

frequency eddy current (HFEC)

inspections to detect cracks of the

forward flange of the support fitting

adjacent to the collars of two fasteners

of the number 1 and number 3 engines;

3. Performing repetitive detail visual

inspections to detect cracks of the upper

and lower flanges adjacent to six

fasteners of the number 1 and number

3 engines;

4. Repairing the cracked forward

support fitting; and

5. Performing a HFEC inspection to

detect cracks of the fastener holes in the

forward support fitting of the number 1

and number 3 engines, and, if possible,

modification of the fastener holes; and

various follow-on actions. (These

follow-on actions include installation of

fasteners, repetitive HFEC inspections,

and repair of cracked forward support

fittings.) The modification involves

oversizing the fastener holes until the

HFEC does not detect any cracks.

Accomplishment of this HFEC

inspection, modification, and follow-on

actions will eliminate the need for the

repetitive pre-modification inspections,

as described in items 1 though 3.

Explanation of the Requirements of the

Rule

Since an unsafe condition has been

identified that is likely to exist or

develop on other Boeing Model 727

series airplanes of the same type design,

this AD is being issued to detect and

correct fatigue cracking of the forward

support fitting, which could result in

failure of the support fitting and

consequent separation of the engine

from the airplane. This AD requires

repetitive pre-modification inspections

to detect cracks of the forward support

fitting of the number 1 and number 3

engines; and repair, if necessary. This

AD also provides for an optional HFEC

inspection, and, if possible,

modification of the fastener holes; and

various follow-on actions.

Accomplishment of these optional

actions constitutes terminating action

for the repetitive pre-modification

inspections. The actions are required to

be accomplished in accordance with the

service bulletin described previously.
9360 Federal Register / Vol. 62, No. 41 / Monday, March 3, 1997 / Rules and Regulations

Differences Between the AD and the

Relevant Service Information

Operators should note that, although

the service bulletin specifies that the

manufacturer must be contacted for

disposition of certain conditions, this

AD requires the repair of those

conditions to be accomplished in

accordance with method approved by

the FAA.

Interim Action

This AD is considered interim action.

The FAA is considering further

rulemaking action to supersede this AD

to require an HFEC inspection to detect

cracks of the fastener holes in the

forward support fitting of the number 1

and number 3 engines, and, if possible,

modification of the fastener holes; and

various follow-on actions.

Accomplishment of these actions will

constitute terminating action for the

repetitive pre-modification inspections

required by this AD action. However,

the FAA’s planned compliance time for

these actions is sufficiently long so that

prior notice and time for public

comment will be practicable.

Determination of Rule’s Effective Date

Since a situation exists that requires

the immediate adoption of this

regulation, it is found that notice and

opportunity for prior public comment

hereon are impracticable, and that good

cause exists for making this amendment

effective in less than 30 days.

Comments Invited

Although this action is in the form of

a final rule that involves requirements

affecting flight safety and, thus, was not

preceded by notice and an opportunity

for public comment, comments are

invited on this rule. Interested persons

are invited to comment on this rule by

submitting such written data, views, or

arguments as they may desire.

Communications shall identify the

Rules Docket number and be submitted

in triplicate to the address specified

under the caption ADDRESSES. All

communications received on or before

the closing date for comments will be

considered, and this rule may be

amended in light of the comments

received. Factual information that

supports the commenter’s ideas and

suggestions is extremely helpful in

evaluating the effectiveness of the AD

action and determining whether

additional rulemaking action would be

needed.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the rule that might suggest a need to

modify the rule. All comments

submitted will be available, both before

and after the closing date for comments,

in the Rules Docket for examination by

interested persons. A report that

summarizes each FAA-public contact

concerned with the substance of this AD

will be filed in the Rules Docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this rule must

submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 97–NM–32–AD.’’ The

postcard will be date stamped and

returned to the commenter.

Regulatory Impact

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.

The FAA has determined that this

regulation is an emergency regulation

that must be issued immediately to

correct an unsafe condition in aircraft,

and that it is not a ‘‘significant

regulatory action’’ under Executive

Order 12866. It has been determined

further that this action involves an

emergency regulation under DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979). If it is

determined that this emergency

regulation otherwise would be

significant under DOT Regulatory

Policies and Procedures, a final

regulatory evaluation will be prepared

and placed in the Rules Docket. A copy

of it, if filed, 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

adding the following new airworthiness

directive:

97–05–08 BOEING: Amendment 39–9952.

Docket 97–NM–32–AD.

Applicability: All Model 727 series

airplanes, certificated in any category.

Note 1: This AD applies to each airplane

identified in the preceding applicability

provision, regardless of whether it has been

otherwise modified, altered, or repaired in

the area subject to the requirements of this

AD. For airplanes that have been modified,

altered, or repaired so that the performance

of the requirements of this AD is affected, the

owner/operator must request approval for an

alternative method of compliance in

accordance with paragraph (e) of this AD.

The request should include an assessment of

the effect of the modification, alteration, or

repair on the unsafe condition addressed by

this AD; and, if the unsafe condition has not

been eliminated, the request should include

specific proposed actions to address it.

Compliance: Required as indicated, unless

accomplished previously.

To detect and correct fatigue cracking,

which could result in failure of the support

fitting and consequent separation of the

engine from the airplane, accomplish the

following:

(a) Within 100 days or within 600 flight

cycles after the effective date of this AD,

whichever occur first, accomplish paragraph

(a)(1), (a)(2), and (a)(3) of this AD, in

accordance with Boeing Service Bulletin

727–54A0010, Revision 4, dated January 30,

1997.

(1) Perform a visual inspection to detect

cracks of the upper and lower flanges, and

the vertical web of the forward support fitting

of the number 1 and number 3 engines, in

accordance with Part 1—Pre-Modification

Inspections of the Accomplishment

Instructions of the service bulletin.

(2) Perform a high frequency eddy current

(HFEC) inspection to detect cracks of the

forward flange of the support fitting adjacent

to the collars of two fasteners of the number

1 and number 3 engines, in accordance with

Part 1—Pre-Modification Inspections of the

Accomplishment Instructions of the service

bulletin.

(3) Perform a detailed visual inspection to

detect cracks of the upper and lower flanges

adjacent to six fasteners of the number 1 and

number 3 engines, in accordance with Part

1—Pre-Modification Inspections of the

Accomplishment Instructions of the service

bulletin.

(b) If no crack is detected during the

inspections required by paragraph (a) of this

AD, repeat those inspections thereafter at

intervals not to exceed 100 days or 600 flight

cycles, whichever occurs first.

(c) If any crack is detected during any

inspection required by paragraph (a) of this

AD, prior to further flight, repair the forward

support fitting in accordance with a method

approved by the Manager, Seattle Aircraft

Certification Office (ACO), FAA, Transport

Airplane Directorate.
Federal Register / Vol. 62, No. 41 / Monday, March 3, 1997 / Rules and Regulations 9361

(d) Accomplishment of the actions

specified in paragraphs (d)(1) and (d)(2) of

this AD in accordance with Boeing Service

Bulletin 727–54A0010, Revision 4, dated

January 30, 1997, constitutes terminating

action for the requirements of paragraphs (a)

and (b) of this AD.

(1) Perform a HFEC inspection to detect

cracks of the fastener holes in the forward

support fitting of the number 1 and number

3 engines, and, if possible, modify the

fastener holes, in accordance with Part II—

Fastener Hole Modification of the

Accomplishment Instructions of the service

bulletin.

(i) If the modification (i.e., a fastener

installed in a hole with no cracks) was

accomplished at all eight holes, no further

action is required by paragraph (d)(1) of this

AD.

(ii) If the modification was not

accomplished at all eight holes because of the

continued detection of cracking, prior to

further flight, repair the forward support

fitting in accordance with a method approved

by the Manager, Seattle ACO.

(2) Prior to the accumulation of 3,000 flight

cycles or 24 months, whichever occurs first,

following accomplishment of paragraph

(d)(1) of this AD, perform a HFEC inspection

to detect corrosion or cracks of the modified

forward support fitting of the number 1 and

number 3 engines, in accordance with Part

III—Post-Modification Inspections of the

Accomplishment Instructions of the service

bulletin.

(i) If no crack or corrosion is detected, prior

to further flight, install the fasteners wet with

a sealant in accordance with the service

bulletin. Repeat the HFEC inspection

required by paragraph (d)(2) of this AD

thereafter at intervals not to exceed 3,000

flight cycles or 24 months, whichever occurs

first.

(ii) If any crack or corrosion is detected,

prior to further flight, repair the forward

support fitting in accordance with a method

approved by the Manager, Seattle ACO.

(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, Seattle

Aircraft Certification Office (ACO), FAA,

Transport Airplane Directorate. Operators

shall submit their requests through an

appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, Seattle ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Seattle ACO.

(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 airplane to

a location where the requirements of this AD

can be accomplished.

(g) The inspections and modifications shall

be done in accordance with Boeing Service

Bulletin 727–54A0010, Revision 4, dated

January 30, 1997. This 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., suite700, Washington,

DC.

(h) This amendment becomes effective on

March 18, 1997.

Issued in Renton, Washington, on February

21, 1997.

James V. Devany,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–4947 Filed 2–28–97; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 94–SW–17–AD; Amendment

39–9950; AD 97–05–06]

RIN 2120–AA64

Airworthiness Directives; Schweizer

Aircraft Corporation and Hughes

Helicopters, Inc. Model 269A, 269A–1,

269B, and TH–55A Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to Schweizer Aircraft

Corporation and Hughes Helicopters,

Inc. Model 269A, 269A–1, 269A–2, and

269B helicopters, that currently requires

initial and repetitive inspections of the

main rotor thrust bearing (bearing) for

bearing rotational roughness, corrosion,

inadequate lubrication, physical

damage, or excessive zinc chromate

paste or moisture. This amendment

requires the same initial and repetitive

inspections required by the existing AD,

but would extend the retirement life for

certain bearings, and would remove the

Model 269A–2 helicopter from, and add

the Model TH–55A helicopters to the

applicability of this AD. This

amendment is prompted by an FAA

analysis of service information issued

by the manufacturer that extends the

retirement life for certain bearings. The

actions specified by this AD are

intended to prevent failure of the

bearing, loss of the main rotor, and

subsequent loss of control of the

helicopter.

DATES: Effective April 7, 1997.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of April 7,

1997.

ADDRESSES: The service information

referenced in this AD may be obtained

from Schweizer Aircraft Corporation,

P.O. Box 147, Elmira, New York 14902.

This information may be examined at

the FAA, Office of the Assistant Chief

Counsel, Room 663, 2601 Meacham

Blvd., 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.

Ray O’Neill, Aerospace Engineer,

Airframe and Propulsion Branch, New

York Aircraft Certification Office, FAA,

New England Region, 10 5th Street,

Valley Stream, New York 11581,

telephone (516) 256–7505, fax (516)

568–2716.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39)

by superseding AD 68–21–05,

Amendment 39–672 (33 FR 15543,

October 19, 1968), which is applicable

to Model 269A helicopters, serial

numbers (S/N) 0011 through 0979

(except Model TH–55A helicopters),

Model 269A–1 helicopters, S/N 0001

through 0041, Model 269A–2 helicopter,

S/N 0001, and Model 269B, S/N 0001

through 0370, as revised by Amendment

39–1055 (35 FR 12532, August 6, 1970),

was published in the Federal Register

on June 17, 1996 (61 FR 30548). That

action proposed to require the same

initial and repetitive inspections

required by the existing AD (inspections

of the main rotor thrust bearing

(bearing) for bearing rotational

roughness, corrosion, inadequate

lubrication, physical damage, or

excessive zinc chromate paste or

moisture), but would extend the

retirement life for certain bearings, and

would remove the Model 269A–2

helicopter from, and add the Model TH–

55A helicopters to the applicability of

this AD.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were received on the

proposal or the FAA’s determination of

the cost to the public. The FAA has

determined that air safety and the

public interest require the adoption of

the rule as proposed, except for editorial

changes and changes to paragraph (a)

that more specifically state the actions

that are required for those bearings

having less than 300 hours time-inservice. The FAA has determined that

these changes will neither increase the

economic burden on any operator nor

expand the scope of the AD.

The FAA estimates that 500

helicopters of U.S. registry will be

affected by this AD, that it will take

approximately 8 work hours per

helicopter to accomplish the required