Leonardo ASB 109K-076: No revision named, text

TextPartly OCR

Some pages are OCR from a scan. OCR can misread letters and numbers.

Query with SQL

duckdb -csv -c "SELECT p.page, p.text_source, p.text, f.rights_holder, f.license
  FROM 'https://openairdocs.org/data/latest/service_document_file_page.parquet' p JOIN 'https://openairdocs.org/data/latest/service_document_file.parquet' f USING (file_sha256)
  WHERE p.file_sha256 = 'dd4d28c2b1df67dea0b6ca3a1c776eb12a4974e24b70e2aeafebb66032b78cfd'
  ORDER BY p.page"

Prints the whole list as CSV. It reads the release’s Parquet files over HTTPS, so there’s nothing to download first. Install DuckDB to run it.

SELECT p.page, p.text_source, p.text, f.rights_holder, f.license
FROM 'https://openairdocs.org/data/latest/service_document_file_page.parquet' p JOIN 'https://openairdocs.org/data/latest/service_document_file.parquet' f USING (file_sha256)
WHERE p.file_sha256 = 'dd4d28c2b1df67dea0b6ca3a1c776eb12a4974e24b70e2aeafebb66032b78cfd'
ORDER BY p.page

Run it at the DuckDB prompt, or in any tool that reads Parquet over HTTPS. More ways to query the release are on Use the data.

Page 1Open in PDF

Pa ge 1 of 38 N° 109K-076 DA TE: March 21, 2023 REV. : / - M arch 15, 2017 TITLE ATA 64 – TAIL ROTOR HOUSING AND SLIDER GROUP DISASSEMBLY AND R

EASSEMBLY

REVISION LOG First Issue An appropriate entry should be made in the aircraft log book upon accomplishment.

If ownership of aircraft has changed, please, forward to new owner.

Leonardo S.p.A.

Via Giovanni Agusta, 520 21017 Cascina Costa di Samarate (VA) Italy Tel.: +39 0331 229111 - Fax: +39 0331 229605/222595 ALERT

SERVICE BULLETIN

Page 2Open in PDF

S.B. N°109K-076 ALERT DATE: March 21, 2023 Page 2 of 38 REVISION: /

1. PLANNING INFORMATION A. EFFECTIVITY Part I:

All A109K2 helicopters that have performed maintenance activities requiring the disassembly of the tail rotor duplex bearing housing after the helicopter delivery.

Part II:

All A109K2 helicopters.

B. COMPLIANCE Part I:

Within and not later than 100 (one hundred) flight hours or 6 (six) months, whichever occurs first, after the issue of this Service Bulletin.

Part II:

At each assembly of the tail rotor duplex bearing housing.

C. CONCURRENT REQUIREMENTS N.A.

D. REASON This Service Bulletin is issued in order to prescribe the disassembly and reassembly of the housing and slider assembly of the tail rotor rotating controls.

E. DESCRIPTION There have been reported cases of ring-nut tighten loss, likely as a result of poor maintenance tasks accomplishment of the assembly instructions for the tail rotor housing and slider group.

In order to minimize the likelihood of occurrence of potential human errors during maintenance, LH updated the maintenance instructions in order to provide additional guidelines, including a better identification Vital Points (VP) for the assembly of the tail rotor duplex bearing support.

As such, this Service Bulletin requires (Part I) to perform the installation of the tail rotor duplex bearing housing following the IETP updated instructions and (Part II) requires to follow such updated instructions whenever the TR duplex bearing housing is assembled.

During the procedure, the operator must obey the Local Regulations applicable to the Vital Points.

Page 3Open in PDF

S.B. N°109K-076 ALERT DATE: March 21, 2023 REVISION: / Page 3 of 38 F. APPROVAL The technical content of this Service Bulletin is approved under the authority of DOA nr.

EASA.21.J.005.

EASA states mandatory compliance with inspections, modifications or technical directives and related time of compliance by means of relevant Airworthiness Directives.

G. MANPOWER To comply with this Service Bulletin, the following MMH are deemed necessary:

Part I: 8 (eight).

Part II: N.A.

MMH are based on hands-on time and can change with personnel and facilities available.

H. WEIGHT AND BALANCE N.A.

I. REFERENCES

1) PUBLICATIONS

SECTION/PARAGRAPH DESCRIPTION PART PAR01 00-20-1 Helicopter Safety I PAR02 64-00-15 Tail rotor hub and blades assy – Removal/Installation I PAR03 64A-00-16 Tail rotor hub and blades assy – Removal/Installation I PAR04 64-00-17 Tail rotor hub and blades assy – Removal/Installation I PAR05 64A-00-18 Tail rotor hub and blades assy – Removal/Installation I PAR06 64-30-5 Pitch change mechanism – Removal/Installation I, II PAR07 64-31-6 Pitch change mechanism – Removal/Installation I, II

2) ACRONYMS & ABBREVIATIONS AMDI Aircraft Material Data Information MM Maintenance Manual DOA Design Organization Approval IETP Interactive Electronic Technical Publications EASA European Aviation Safety Agency LH Leonardo Helicopters PTUM Pictorial Tools Usage Manual

Page 4Open in PDF

S.B. N°109K-076 ALERT DATE: March 21, 2023 Page 4 of 38 REVISION: / MMH Maintenance Man Hours P/N Part Number S/N Serial Number

3) ANNEX Annex A A109K2 MM Section 64-30 Rev. 5.

Annex B A109K2 10001 thru 10015 and 10027 MM Section 64-31 Rev. 6.

J. PUBLICATIONS AFFECTED N.A.

K. SOFTWARE ACCOMPLISHMENT SUMMARY N.A.

Page 5Open in PDF

S.B. N°109K-076 ALERT DATE: March 21, 2023 REVISION: / Page 5 of 38

2. MATERIAL INFORMATION A. REQUIRED MATERIALS

1) PARTS N.A.

2) CONSUMABLES Refer also to AMDI for the consumable materials required to comply with the MM Paragraphs referenced in the accomplishment instructions.

3) LOGISTIC MATRIX N.A.

B. SPECIAL TOOLS Refer to PTUM for the special tools required to comply with the MM Paragraphs referenced in the accomplishment instructions.

C. INDUSTRY SUPPORT INFORMATION N.A.

Page 6Open in PDF

S.B. N°109K-076 ALERT DATE: March 21, 2023 Page 6 of 38 REVISION: /

3. ACCOMPLISHMENT INSTRUCTIONS

GENERAL NOTES

a) Place an identification tag on all components that are re-usable, including the attaching hardware that have been removed to gain access to the modification area and adequately protect them until their later re-use.

b) Shape the cables in order to prevent interference with the structure and the other existing installations, using where necessary suitable lacing cords and plastic cable tiedown.

PART I

1. In accordance with MM Paragraph 00-20-1, prepare the helicopter on ground for a safe maintenance. Disconnect the battery, all electrical power sources and/or the external power supply.

2. In accordance with MM Paragraph 64-00-15 or 64A-00-16 for A109K2, or with MM Paragraph 64-00-17 or 64A-00-18 for A109K2 10001 thru 10015 and 10027, remove from the helicopter the tail rotor hub and blades assembly.

3. In accordance with MM Paragraph 64-30-5 for A109K2, or MM Paragraph 64-31-6 for A109K2 10001 thru 10015 and 10027, remove the tail rotor pitch change mechanism.

4. In accordance with MM Paragraph 64-30-5 for A109K2, or MM Paragraph 64-31-6 for A109K2 10001 thru 10015 and 10027, disassemble the tail rotor housing and slider assembly.

NOTE Vital Point (VP): the point of a component, assembly or installation, where incorrect assembly or an undetected error could cause the loss of rotorcraft and/or fatalities.

5. In accordance with MM Paragraph 64-30-5 Rev. 5 fo r A109K2 or MM Paragraph 64-31-6 Rev. 6 for A109K2 10001 thru 10015 and 10027 (Ref. Leonardo WebPortal or Annex A and/or Annex B of this Service Bulletin), assemble the tail rotor housing and slider assembly.

6. In accordance with MM Paragraph 64-30-5 for A109K2, or MM Paragraph 64-31-6 for A109K2 10001 thru 10015 and 10027, install the tail rotor housing and slider assembly.

7. In accordance with MM Paragraph 64-00-15 or 64A-00-16 for A109K2, or with MM Paragraph 64-00-17 or 64A-00-18 for A109K2 10001 thru 10015 and 10027, install on the

Page 7Open in PDF

S.B. N°109K-076 ALERT DATE: March 21, 2023 REVISION: / Page 7 of 38 helicopter the tail rotor hub and blades assembly.

8. Return the helicopter to a ready to flight condition and record for compliance with Part I of this Service Bulletin on the helicopter logbook.

9. Send the attached compliance form to the following mail box:

engineering.support.lhd@leonardo.com As an alternative, gain access to My Communications section on Leonardo WebPortal and compile the “Service Bulletin Application Communication”.

Page 8Open in PDF

S.B. N°109K-076 ALERT DATE: March 21, 2023 Page 8 of 38 REVISION: /

PART II NOTE Vital Point (VP): the point of a component, assembly or installation, where incorrect assembly or an undetected error could cause the loss of rotorcraft and/or fatalities.

1. During the application of any maintenance operati on requiring the assembly of the TR duplex bearing housing, it is required to perform the relevant assembly procedure in accordance with MM Paragraph 64-30-5 Rev. 5 for A109K2 or MM Paragraph 64-31-6 Rev. 6 for A109K2 10001 thru 10015 and 10027 (Ref. Leonardo WebPortal or Annex A and/or Annex B of this Service Bulletin) or later published issues.

2. Record for compliance with Part II of this Service Bulletin on the helicopter logbook.

3. Send the attached compliance form to the following mail box:

engineering.support.lhd@leonardo.com As an alternative, gain access to My Communications section on Leonardo WebPortal and compile the “Service Bulletin Application Communication”.

 Non cancellare mai questo segnalibro Non cancellare mai interruzione sezione 

Page 9Open in PDF

ANNEX A S.B. N°109K-076 ALERT DATE: March 21, 2023 REVISION: / Page 9 of 38

ANNEX A A109K2 MM SECTION 64-30 REV. 5

Page 10OCROpen in PDF

LEONARDO

ANNEX A HELICOPTERS A109K2-MM _ MAINTENANCE MANUAL A109K2

HELICOPTER MODEL THIS 2nd ISSUE ENTIRELY SUPERSEDES ISSUE DATED 16th OCTOBER 1995 INCLUDING REVISION 15 DATED 15 SEPTEMBER 2010 Second Issue: 20th May 2014 Revision: No. 5 - 10th March 2023 THIS PUBLICATION IS ISSUED BY LEONARDO S.p.A.

This document contains proprietary data and information and shall not be disclosed, reproduced in whole or in part for any purpose, other than helicopter operation or maintenance, without prior written authorization from LEONARDO S.p.A.

PUBLICATION CODE 502051275 S.B. N°109K-076 ALERT DATE: March 21, 2023 Page 10 of 38 REVISION: /

Page 11OCROpen in PDF

ANNEX A * LEONARDO HELICOPTERS A109K2-MM SECTION 64-30

PITCH CHANGE MECHANISM 64-30-1. DESCRIPTION 64-30-2. PITCH CHANGE MECHANISM The pitch change mechanism, mounted on the 90° gearbox, consists of a sleeve sliding on the 90° output shaft, connected to the tail rotor blades by a slider and two pitch links, and to the control pedals by links and levers.

The components of the pitch change mechanism are shown in figure 64-19.

64-30-3. MAINTENANCE 64-30-4. PITCH CHANGE MECHANISM 64-30-5. Removal/installation (Fig 64-19) A. Input Conditions

(1) Required conditions:

- Helicopter safe for maintenance (Chap 00).

- Access panels 11 and 60 removed (Sect 06-40, fig 06-4).

- Tail rotor hub and blade assembly removed (Sect 64-00).

(2) Support equipment:

- Tool, T/R pitch change slider ring nut removal/installation (LSE NO 10).

- Tool, T/R pitch change housing ring nut removal/installation (LSE NO 11).

Tool, T/R pitch change housing duplex bearing removal (LSE NO 12).

Tool, T/R pitch change housing duplex bearing installation (LSE NO 13).

- Tool, T/R pitch change slider removal (LSE NO 14).

- Ring, T/R slider bushing installation (LSE NO 19) .

- Syringe (Local supply).

- Heating gun (Local supply).

- Feeler gage (Local supply).

- Depth micrometer gage (Local supply).

- Refrigerator (Local supply).

Rev. 5 64-1 S.B. N°109K-076 ALERT DATE: March 21, 2023 REVISION: / Page 11 of 38

Page 12OCROpen in PDF

K LEONARDO

ANNEX A HELICOPTERS A109K2-MM

(3) Consumable materials:

WARNING: THE CONSUMABLE MATERIALS THE NOMENCLATURE OF WHICH IS PREFIXED BY "(D)" ARE DANGEROUS MATERIALS.

BEFORE USE, MAKE SURE TO KNOW THE SAFETY PRECAUTIONS AND FIRST AID INSTRUC- TIONS PRINTED ON:

- THE LABEL ON THE CONTAINER THE MATERIAL WAS SUPPLIED IN

- THE MATERIAL SAFETY DATA SHEET

- THE LOCAL SAFETY REGULATIONS.

ALSO MAKE SURE THAT THE APPLICABLE FIRST AID MATERIALS ARE AVAILABLE.

- (D) MEK (C005).

- (D) Sealing compound (C029).

Safety wire (C014).

(D) Primer (C446).

(D) Grease (C594).

Soft lint-free cloth (C011).

(D) Solvent, cleaning (C023).

(D) Oil (C139).

(D) Primer (C237).

(4) Other recommendations:

WARNING: THIS INSTALLATION INCLUDES VITAL POINTS (VP). DURING THE PROCEDURE, YOU MUST OBEY THE LOCAL REGULATIONS APPLICABLE TO THE VITAL POINTS.

CAUTION: MAKE SURE THAT YOU DO NOT MIX GREASES OF DIFFERENT BRANDS ALTHOUGH THE SPECIFICATIONS ARE THE SAME. REFER TO THE HELICOPTER LOG BOOK TO PREVENT MIXTURE OF UNWANTED GREASES.

CAUTION: THIS COMPONENT INCLUDES CRITICAL PARTS. EXAMINE THE COMPONENT FOR SIGNS OF

STRUCTURAL DAMAGE, BEFORE YOU INSTALL IT ON THE HELICOPTER B. Removal Procedure.

(1) Disconnect tail rotor pitch control tube (59) from lever (49) by removing attaching hardware. Discard cotter pin.

(2) Disconnect forward link (30) from sleeve (27) and aft link (35) from slider (23) by removing attaching part.

Discard cotter pins.

(3) Detach link (35) from link (30) by removing attaching parts. Discard cotter pin.

(4) Cut lockwire from forward boot (26) and withdraw sleeve (25) from gearbox shaft. Remove forward boot (26) from sleeve (25). If loose remove bushing (27) ref to para 64-30-11.

NOTE: Mark position of links (20) to reconnect in same position during reassembly on slider.

(5) Disconnect link (20) from slider (23) by removing parts; remove link (20). Discard cotter pin.

(6) Remove links (10) by removing attaching parts. Discard cotter pins.

64-2 Rev. 5 S.B. N°109K-076 ALERT DATE: March 21, 2023 Page 12 of 38 REVISION: /

Pages 13–24 of 39